Efficient systems and methods for construction and operation of accelerating machines

ABSTRACT

In embodiments of the present invention improved capabilities are described for the efficiency with which fluid energy is converted into another form of energy, such as electrical energy, where an array of fluid energy conversion modules is contained in a scalable modular networked superstructure. In certain preferred embodiments, a plurality of turbines, such as for instance wind turbines, may be disposed in an array, where the plurality of arrays may be disposed in a suitable arrangement in proximity to each other and provided with geometry suitable for tight packing in an array with other parameters optimized to extract energy from the fluid flow. In addition, the turbines may be a more effective adaptation of a turbine, or an array of turbines, to varying conditions, including fluid conditions that may differ among different turbines in an array, or among different turbines in a set of arrays.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of U.S. provisional application61/121,412, filed Dec. 10, 2008, which is hereby incorporated byreference in its entirety.

This application is a continuation-in-part of U.S. patent applicationSer. No. 12/332,313, filed Dec. 10, 2008 which claims benefit to U.S.provisional application 61/012,759, filed on Dec. 10, 2007, each ofwhich is incorporated by reference in its entirety.

The following application is also related to this disclosure: U.S. App.No. 61/285,381 filed on Dec. 10, 2009, which is incorporated byreference in its entirety.

FIELD OF INVENTION

The present invention is related to energy conversion, and in certainpreferred embodiments to the energy conversion from a fluid flow, suchas wind, to another type of energy, such as electrical energy.

BACKGROUND

The conversion of energy from a fluid flow, such as from the wind, toelectrical energy has been typically implemented in the past with largesingular horizontal axis turbines. The energy conversion efficiency forsuch a configuration may be limited. As alternate energy sources such aswind energy are increasingly utilized to counter the rising energy costsof fossil fuels, it becomes more vital that energy efficienciesassociated with these alternate energy sources be maximized. A needexists for improved methods and systems for converting energy from afluid flow to electrical energy.

SUMMARY

In embodiments of the present invention improved capabilities aredescribed for the efficiency with which fluid energy is converted intoanother form of energy, such as electrical energy, where an array offluid energy conversion modules is contained in a scalable modularnetworked superstructure. In certain preferred embodiments, a pluralityof turbines, such as for instance wind turbines, may be disposed in anarray, where the plurality of arrays may be disposed in a suitablearrangement in proximity to each other and provided with geometrysuitable for tight packing in an array with other parameters optimizedto extract energy from the fluid flow. In addition, the turbines may bea more effective adaptation of a turbine, or an array of turbines, tovarying conditions, including fluid conditions that may differ amongdifferent turbines in an array, or among different turbines in a set ofarrays.

Methods and facilities are described herein that may allow a moreefficient construction or operation of accelerating machines. These mayapply in general to the conversion of fluid energy into power, increaseor stabilization of machine yield, the cost-efficient construction ofthe mechanisms necessary to convert fluid energy into power, and thelike. Structures and methods pertaining to the installation, structuralsupport, operation, and the like, of accelerating arrays are disclosed.Alternative methods of extracting energy from a fluid flow aredescribed. Additionally methods are disclosed of optimizing therelationship of rotor profile, loading, tip speed in higher velocityenvironments as are found in a nozzle throat, and the like.Additionally, methods are disclosed for optimizing the cost-yieldrelationship with regard to the installation, operation, maintenance,and the like, of accelerating machines to produce the lowest cost ofenergy within the parameters of achievable embodiments. Additionallyfurther methods of modeling and optimizing accelerating nozzles andtheir respective flow related components are disclosed.

These and other systems, methods, objects, features, and advantages ofthe present invention will be apparent to those skilled in the art fromthe following detailed description of the preferred embodiment and thedrawings. All documents mentioned herein are hereby incorporated intheir entirety by reference.

BRIEF DESCRIPTION OF THE FIGURES

The invention and the following detailed description of certainembodiments thereof may be understood by reference to the followingfigures:

FIG. 1 depicts a kinetic access facility.

FIG. 2 depicts a kinetic access facility array.

FIG. 3 depicts a square polygon expansion exit, module, and array.

FIG. 4 depicts a complex topography connector and members.

FIGS. 5A and 5B depict examples of structural members of variabledensity and profile.

FIGS. 6A and 6B depicts linear scalloping on a surface and in profile.

FIG. 7 depicts an 85 m×51 m uniform array compared with the same area ofa 75 m horizontal axis wind turbine.

FIG. 8 depicts a 100 m×44 m uniform array compared with the same area ofa 75 m horizontal axis wind turbine.

FIGS. 9A and 9B depicts a series of arrays side and front elevations.

FIG. 10 depicts non-uniform array with orientation tails.

FIG. 11 depicts an array with three integrated generators.

FIG. 12 depicts an integrated generator-module example.

FIG. 13 depicts an array with storage.

FIG. 14 depicts a module in a triangular superstructure.

FIG. 15 depicts components of a nozzle.

FIG. 16 depicts two nozzles in a serial arrangement.

FIG. 17 depicts a side elevation of a hexagonal nozzle.

FIG. 18 depicts a nozzle with a circular throat and polygonal exit.

FIG. 19 depicts two nested nozzles.

FIG. 20 depicts a superstructure connector.

FIG. 21 depicts a horizontal axis wind turbine generator arrangement.

FIG. 22 depicts a superstructure and module arrangement for hexagonalmodules.

FIG. 23 depicts a space frame for a square array.

FIG. 24 depicts examples of nozzle polygon entrances.

FIG. 25 depicts an example of power transfer in a square array.

FIG. 26. depicts a diagram of an initial intake momentum vector.

FIG. 27 depicts a nozzle with truncation intake and exit.

FIG. 28 depicts a nozzle with truncated intake and 1/r−0 interpolatedcurvature.

FIG. 29 depicts an arc section diagram for inlet geometry.

FIG. 30 depicts a multi-blade configuration

FIG. 31 depicts a 3-blade rotor efficiency plot.

FIG. 32 depicts a plot of annual velocity distribution.

FIG. 33 depicts an annual distribution power output by linear velocity.

FIG. 34 depicts annual distribution with heavier loading to shift.

FIG. 35 depicts open position 12 blades, where velocity is approximatelyin the range of 1-3 m/s.

FIG. 36 depicts open position 6 blades, where velocity is approximatelyin the range of 3-6 m/s.

FIG. 37 depicts closed position 3 blades, where velocity isapproximately 6+m/s.

FIG. 38 depicts a sample of open and closed profiles.

FIG. 39 depicts a rotor consisting of a rotatable body with a centralmass reservoir.

FIG. 40 depicts a weighted structure initial position.

FIG. 41 depicts a weighted structure in a subsequent position.

FIG. 42 depicts a 3 blade structure in motion.

FIG. 43 depicts a 3 blade structure with mass control channel andcentral mass reservoir.

FIG. 44 depicts an embodiment of a fractal space frame.

FIG. 45 depicts an embodiment of a configuration of a fractal spaceframe where the additional members may be added.

FIG. 46 depicts an embodiment of a 3 iteration octahedral space frame.

FIG. 47 depicts an embodiment of an accelerating array.

FIG. 48A-B depicts embodiments of structural members.

FIG. 49 depicts an embodiment of a single “mast” frame.

FIG. 50 depicts an embodiment of an array 5004 and a portion of anexterior structure.

FIG. 51A-E depict exterior superstructures with polygonal variation.

FIG. 52 depicts a structure with basis polygon and polyhedral members.

FIG. 53 depicts a structure with basis polygon and polyhedral membersmounted with a bearing.

FIG. 54 depicts an isometric nozzle with bulbed throat.

FIG. 55 depicts nozzle cross section profiles.

FIG. 56 depicts drill through examples.

FIG. 57 depicts example blade shapes.

FIG. 58 depicts example blade shapes.

FIG. 59 depicts example blade shapes.

FIG. 60 depicts a cost-yield optimization flow chart, in an embodimentof the present invention.

FIG. 61 depicts an embodiment of elements affecting annual yields.

FIG. 62 depicts an embodiment of a conversion matrix.

FIG. 63 depicts an embodiment of an acceleration matrix.

FIG. 64 depicts an embodiment of a mass throughput efficiency matrix.

FIG. 65 depicts an embodiment of a nozzle efficiency row matrix.

FIG. 66 depicts an embodiment of a rotor efficiency matrix.

FIG. 67 depicts an embodiment of an RPM-load parameters matrix for agenerator.

FIG. 68 depicts an embodiment of a nozzle-rotor pair matrix.

FIG. 69A-B depicts an embodiment of a radial velocity machine.

FIG. 70 depicts a fluid cooled generator embodiment.

FIG. 71 depicts a wind power module optimization algorithm embodiment ofthe present invention.

FIG. 72 depicts a wind power support structure embodiment of the presentinvention.

FIG. 73. depicts a wind power nozzle embodiment of the presentinvention.

FIG. 74. depicts a wind power support structure embodiment of thepresent invention.

FIG. 75 depicts a wind power system embodiment of the present invention.

FIG. 76 depicts a wind power system cost yield optimization algorithmembodiment of the present invention.

While the invention has been described in connection with certainpreferred embodiments, other embodiments would be understood by one ofordinary skill in the art and are encompassed herein.

All documents referenced herein are hereby incorporated by reference.

DETAILED DESCRIPTION

The present invention may be comprised of an n×m modular array having aplurality of energy producing modules (in certain preferred embodiments,wind turbines) arranged in the array and oriented with respect to afluid flow, with a plurality of modular energy conversion unitsoptimally placed in a given array configuration to maximize energyoutput.

In embodiments, the fluid flow toward which the array is oriented may bepreferably a natural or artificial generated differential flow, such aswind, solar chimney, a differential tunnel flow, and the like in thenatural case, or in the artificial case, but may also be a “wake” flowor its inverse that is generated by a motive force, such a tide,rotation, fluid, gas displacement, and the like. FIG. 1 depicts anembodiment of the invention, showing components of four representativemodules 110 in an array 124 with superstructure and electricalinfrastructure, including a nozzle facility 104 (which in turn may havestructural characteristics and an orientation facility), a kineticenergy access facility 108 (which may include a rotor, such as withblades and a hub), a drive facility 112 (such as a transmission drivefacility), a generator 122, structure 102, orientation facility 114,blades 118, hub 120, and the like. In embodiments, the array 124 ofmodules 110 may be associated with an integrated or non-integratedsuperstructure and electrical infrastructure that may interface withenergy handling facilities 130 and energy storage facilities 132. Itshould be understood that any number of modules 110 might be provided inan array 124, with optimal arrays 124 possibly including far more thanfour modules 110.

As depicted in FIG. 1, a bearing 128, such as a ball roller bearing, andthe like, or such as a material property bearing, such as a Teflonbearing or the like, or a fluid bearing, magnetic bearing, monolithicbearing such as a cone/ball bearing, and the like, or some combinationbearing having all or a portion of the properties of these bearings maybe used to support an array of modules, such as to allow the array torotate about a vertical axis, allowing the array to be oriented (or toself-orient, as described below in certain preferred embodiments) withrespect to a direction of fluid flow. In the case where a magneticbearing or similar bearing structure is used, the bearing structure maygenerate additional energy either for immediate use or for temporarystorage. The drive facility and generator may be associated with anelectrical infrastructure including a conducting medium such asconductive metals, conductive fluids, and the like, such asmagnetorhetological fluids, ferrofluid, superconductors, and the like,or a conducting gas., which may be integrated or associated with thesuperstructure of the array, so that energy from the modules may bepassed to an external energy handling facility, and optionally to alocal or global energy storage facility, such as a flywheel, compressedair, gravitational storage (pumping fluid, gas or solids up a heightdifferential), battery, plurality of batteries, and the like to anenergy conversion facility, such as an electrolysis hydrogen and oxygenproduction facility, or some combination of transport, end-use, storage,facilities, and the like. In embodiments, the magnetic propertiesassociated with electrical distribution or transmission system may beutilized to help orient the array, such as in generator rotor (e.g. usethe magnetic properties of the electrical flow to excite a stator thatcontains the transportation facility).

Referring to FIG. 2, arrays 124 such as those described in connectionwith FIG. 1, each containing a plurality of modules 110, may in turn beconfigured into a plurality of arrays 124, arranged with respect to eachother and oriented with respect to a direction of fluid flow. FIG. 2shows one possible view of four arrays 124 configured in a checkerboardpattern, which is one preferred embodiment of a grouping of arrays 124.In embodiments, arrays 124 may be arranged in a number of combinations,such as the checkerboard described herein, which may use a matrix todivide a given site. One option may be a diamond pattern with spacingranging from the 1×1 checkerboard implementation to an n×mimplementation where the 1−n may refer to the number of cells by whichthe diamond is formed. Another option may be a curved arrangementwherein the rate of curvature can range from 0 to 1 with the spacingstructure ranging from 1 to n. Alternatively the matrix may be filledcompletely dependent on the particular properties of the arrays deployedin the formation. Additionally the arrays may be co-mounted on singularsubstructures in any of the distributions of machines described herein.In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array maybe configured with arrays located in a matrix arrangement with aplurality of similar arrays, such as embodied in a checkerboard pattern,a diamond pattern, a regular pattern, an irregular pattern, a curvedpattern, filled pattern, and the like.

As shown in FIG. 3, the n×m modular array 302 may be comprised of ascalable modular networked superstructure providing both support for atleast one module and the facility for power control, management, andcollection of power from individual modules, and conversion and transferof said power to either a plurality of storage units, a grid, or acombination thereof. In embodiments, the present invention may providean array of nozzles adapted to generate electrical power from the flowof air, where the array may be supported by a scalable modularsuperstructure. The superstructure may be a modular assembly employing ashape such as a space frame type, geodesic, orthogonal, and the like.The superstructure may be of a nozzle-structural integrated type, suchas a flexible pressure based integrated structure, a rigid cellintegrated structure, and the like. The superstructure elements may beconnected by a connection facility such as a weld, a glue, a contactfusing facility, a locking mechanism, and the like. In embodiments, thesuperstructure may include structural components and connectors whichcan be assembled on-site. The superstructure and its elements may have acomplex local and global 3 dimensional topography, such as to maximizeload bearing properties, minimize material use, minimize materialweight, and the like. Structural members of the superstructure may havea uniform circular profile, polygonal profile, elliptical profile,square profile, triangular profile, n-pointed star profile, and thelike. Structural members of the superstructure may have a variableprofile, such as with linear scalloping, radial curvature variability,elliptical curvature variability, square variability, and the like. Themembers of the superstructure may be an isotruss type variable soliditystructure. The elements of the superstructure may include at least oneof a polymer, composite, metallic foam, composite foam, alloy, and thelike.

FIG. 4 shows an embodiment of a complex topography connector and members402. In embodiments, this may provide an example of complex moldtopography intended to reduce material use and maximize structuralproperties, and take the form of surface structures, profiles, variablesolidity structures, and the like.

FIG. 5 shows embodiments of structural members 502A and 502B. Theseexamples may be of structural members of variable density and profile.These may represent a subset of possible complex topography members. Forexample, the member 502A one on the left may be made by filamentwinding, and the member 502B to the right may be extruded or moldedfiber reinforced plastic.

FIG. 6 shows an embodiment of linear scalloping, such as for a wallnozzle, structural member, and the like. This may provide a complex wallfor the nozzle, structural member, and the like. The depiction of linearscalloping 602A to the left represents a scalloping surface orientation,and the depiction of linear scalloping 602B to the right represents thescalloping in a profile view.

The superstructures, may be self-orienting (such as due to the shape ofthe nozzle) and may include methods or systems to mechanically (asdescribed herein) or otherwise control the orientation of the array, orof a module within the array, with regard to the direction of the fluidflow in a fixed implementation. Methods of mechanical orientation mayinclude yaw motors, stored energy flywheels, and the like, or othermethods known in the art. Alternately, they may be mounted onto a mobileplatform to seek out optimal flow conditions. In embodiments, thepresent invention may provide an array of nozzles adapted to generateelectrical power from the flow of air. The array may includeself-orienting nozzles, self-orienting nozzles configured with anon-mechanized element that uses airflow to orient the nozzles,self-orienting nozzles with independent orientation at differentlocations in the array, and the like. The array may include a nozzlecapable of orientation to a vertical component of airflow. Inembodiments, the present invention may provide a nozzle adapted for usein a wind power generating turbine. The nozzle may be configured to becapable of orientation to a vertical component of the wind. In addition,the nozzle may be self-orienting relative to the direction of the wind,such as when there is a tail on the nozzle.

The superstructure may be supported by a number of methods and systemsdepending on the nature of the flow, such as floatation suspension,tower/towers, building integration, cable suspension, and the like.Additionally arrays may be fabricated of materials that enable a lighterthan air implementation. In embodiments, the present invention mayprovide an array of nozzles adapted to generate electrical power fromthe flow of air, where the array may be supported by a scalable modularsuperstructure. The superstructure may be a suspension type ofsuperstructure, supported by a lighter-than-air mechanism, and the like.In embodiments, the present invention may be mounted on land or at sea,attached to existing structures such as a building, bridge, tower, andthe like, or stand alone as a dedicated structure.

The superstructure may be executed as a separate modular supportstructure inclusive of the method of load bearing and powerdistribution. The superstructure elements may also be integrated intothe nozzle structure such that the module becomes a wholly containedelement. In this case the preferred superstructure may provide acolumnar method of plugging the integrated module into the power system.In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may be supported by a scalable modular superstructure. Thesuperstructure may be of a variable type, such as with regard to loadbearing properties, structural properties, and the like. The elements ofthe superstructure may be of a uniform type with regard to load bearingproperties, structural properties, and the like. The elements of thesuperstructure may be variably adapted to the lowest cost solution forlocal load bearing parameters within the array. In embodiments, thesuperstructure may be rigid, may have global flexing mechanisms toaccommodate live loading, may have local flexing mechanisms toaccommodate live loading, and the like.

As shown in FIG. 7 and FIG. 8, the array implementation may providevarious advantages. First it may allow the modules to cover any givenarea without being subject to the inefficiency introduced by the lengthof an efficient divergent component. Secondly the implementation neednot be uniform as in a horizontal-axis wind turbine (HAWT). By housingthe n×m modular array in such a superstructure, the structural upperlimit of flow area or plane a system can cover and gather energy frommay be substantially increased. By covering, say, a rectangular area,the upper rows of an array may be producing energy, if wind is themedium, potentially at a substantially faster mean velocity than lowermodules (because the wind is greater at the top of the array than it iscloser to the ground). This means that in addition to the increasesengendered by the modules, the array structure itself may engender anincrease. In this regard, if the medium is wind, a structure wherein theheight is greater than the width may be the most efficient use of theplane for energy production with the multiple of power productionincreasing as the height value increases from a baseline wherein theheight value is less than the width value. For example, both FIG. 7 andFIG. 8 depict a HAWT 702 that has a 75 meter diameter circular sweeparea of approximately 4400 sq. m., and with a hub height of 50 m with awind speed of 6 m/s. In FIG. 7 the array implementation 704 has anequivalent swept area provided with a 50 meter wide array area with thelowest row at 30 meters and wind speed of 5.4 m/s, and an upper row at117 meters with a wind speed of 7.6 m/s. In FIG. 8, the same swept areais accommodated with an array implementation 802 of the same lowerheight and wind speed, but this time with a narrowing 44 m width andhigher upper row, now with an elevated wind speed f 8.1 m/s. Inembodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array maybe of variable width at different heights. The depth of the array may beless than or equal to the width of the array, such as greater than orequal to the width of the array, more than about 1.25 times the width ofthe array, more than about 2 times the width of the array, and the like.

In this system the dynamic pressure acting on the structure may bedistributed equally through the structure as opposed to being focused ona propeller root or tower as in most horizontal axis machines therebyexpanding the overall swept area that can be covered per linear foot ofmachine width. Additionally, nozzle efficiency may reduce dynamicpressure on the structure. The determination of the number of modules ina given array implementation may be predicated on the necessary nozzlelength ratio, structural loading, and desired energy output.

Some array geometries, such as rectangular/square, triangular,trapezoidal, or a combination or inversion thereof (e.g. and invertedtrapezoid or a hexagon), in the x,y dimensions may maximize wind planeusage relative to cost. Note that a non-uniform x,y implementation wouldalso fall within the scope of the present invention. Structure in the zdimension may be implemented as a uniform or non-uniform plane, withcurvature either of equal or variable depth, or the like. An array ofdimensions wherein said wind facing plane is equal to or greater thanthe depth may provide improved performance in terms of area utilization.In embodiments a configuration wherein the flow-facing width of themachine is greater than depth may provide similar plane coverage asfreestanding rotor systems. FIG. 9 depicts a series of arrays side andfront elevations 902A and 902B. In addition, superstructures may bemounted to a platform singly or in series in the z dimension.

Modules mounted in the superstructure may be comprised of a nozzleconfiguration, a single or plurality of energy capture device/s, asingle or plurality of flow enhancement surface structures, and thelike. The modules and modular elements of the superstructure may be“plug and play” devices allowing maintenance or refitting of the arraycomponents to be performed on- or offsite.

Module nozzle geometry may be optimized, based on uniqueintake-to-throat geometry, exit geometry, volumetric ratios, and arevised theory of fluid dynamic forces, to maximize plane usage,minimize forward and inlet overpressure, entrain and accelerate highpercentage flows with at least one optimized fascia to maximize flowestablishment, and the like. The nozzle may further be of variablegeometry to adapt velocity conditions in the nozzle configurationrelative to ambient velocity conditions and help stabilize said velocitywithin a desired operating range. The variable intake geometry andnozzle configuration geometry may be executed as a single fascia or witha plurality of dependent and independent fascia depending on module sizeand/or the properties of a given fluid. In embodiments, the presentinvention may provide an array of nozzles adapted to generate electricalpower from the flow of air. The array may include nozzles of variablesize, nozzles of variable type, and the like. For instance, variationmay relate to constriction rates of the nozzles and or the powergeneration characteristics of the nozzles. The array may include nozzlesof a shape represented by truncation of a catenoid and the nozzlesshaped to facilitate air flow at the entrance of the nozzles. The arraymay be a packed array of nozzles of variable intake shapes, such ashexagonal intake shapes, triangular intake shapes, square intake shapes,octagonal intake shapes, and the like.

Nozzles additionally may be implemented in either single or multistageconfigurations inclusive of reaccelerating or pressurizing a fluid flowwithin or exterior to the module for additional use in energyproduction. Both uniform and non-uniform execution of the array withregard to nozzle geometry and constriction fall within the scope of theinvention. In embodiments, the present invention may provide an array ofnozzles adapted to generate electrical power from the flow of air. Thearray may include nozzles configured in series relative to the directionof airflow, configured in a nested series, and the like.

Module energy conversion may be comprised of a plurality of kineticenergy conversion devices, such as single or multi-blade rotors, orother facility for kinetic energy conversion, coupled with a facilityfor producing a usable form of power such as a generator, a transmissionand a generator, multiple generators and a usable form of powerelectronics, and the like, to control the loading parameters under whichthe conversion facility operates and to convert or condition the powerproduced into a usable form by whatever end-use facility may beintended, such as a local grid, national grid, storage, or the like. Inembodiments, the conversion may be devices adapted specifically to theoptimized and variable properties of the nozzle configuration and moduledesign, wherein the KE conversion and energy producing devices may beintegrated to the particular parameters of an embodiment to optimize useof the flow.

To maximize energy production relative to cost across a broad range ofwind velocities, a variable blade number rotor may be used as the methodof kinetic energy (KE) conversion. In the case of a variable bladenumber rotor, a self- or mechanically folding blade design may be used,wherein the number of blades is reduced by slotting a divisible numberof blades into the preceding blades in the series. Rotors with differentnumbers of blades and different profiles may have performance profilesthat closely fit a given flow velocity range. Since it is desirable tooptimize the power output of a flow driven power device, a rotor thatadapts the disc solidity presented to the flow may be more efficient atgathering power in the lower speed regimens, and/or under high loadconditions, than a fixed solidity rotor. A variable solidity rotor mayhave a plurality of prime number rotors sets, for example 2, 3, 5, andthe like. Rotor sets may be mounted to a series of dual position sliprings wherein when the dynamic force on a given set is exceeded the ringmay be released and dynamic force on the blades may shift it to a closedposition on the following set of blades. In embodiments, a mechanism maybe slotted on closure such that when the dynamic force on the closedblade sets indicates a drop in velocity the blade set is released toopen position. In embodiments, the present invention may provide anarray of nozzles adapted to generate electrical power from the flow ofair. In embodiments, a rotor may be configured to operate within a windpower generating turbine, where the rotor is configured to present avariable number of blades. In embodiments, the number of blades onrotors of nozzles of the array may vary from one nozzle to other nozzle.

Additionally an “inertial” rotor is described wherein the rotationalmomentum of the blades may be manipulated to alter the inertia of rotor.

Additionally the rotor generator relationship may be executed as in aHAWT wind turbine, with the generator or generators receiving theirmotive force from a central shaft either directly or through a geareddesign, as a fully integrated implementation, as an integratedcomponent, and the like.

In a fully integrated implementation the nozzle itself may constitutethe generator, wherein the rotor blades may be manufactured as induced,excited, permanent magnet rotors, or with a magnetic fluid such asmagneto-rheological fluids and the stator is integrated into the nozzlemold, and the like. An alternative implementation may be one wherein therotor is attached to a magnetic bearing of the same diameter as thethroat to generate power. Another may be the rotor attached to a bearingof the same diameter as throat that is geared on the outward face todrive a plurality of generators surrounding the throat area.

Pressure gradient (PG) enhancement devices/techniques may be usedthroughout modules and the superstructure to perform the task of bothlocal and global gradient enhancement with respect to flow through themodules and superstructure. PG enhancement may be performed by utilizingproperties of thermo and fluid dynamics to create regions of additionalfluid sparsity thereby engendering enhanced local and global gradientdifferentials and allowing the establishment of higher percentage flowsthrough a given module configuration. In addition, a method of achievingdirectional suction pressure may also be used to enhance the rate ofsystem flow.

Due to the wake profile of the nozzles they may be placed in a wind-farmarray in a series of more efficient patterns than is possible withcurrent generation technology, as described herein. For instance, afilled or binary checkerboard pattern may maximize cost to benefit andland use. Additionally, a method of efficient energy storage andintegration of buildings and arrays is disclosed herein.

FIGS. 9-22 depict various aspects of the invention. FIG. 9 depicts aseries of arrays side and front elevations 902A and 902B. FIG. 10depicts non-uniform array with orientation tails in side elevation1002A, top view 1002B, and front elevation 1002C. FIG. 11 depicts anarray 124 with nozzles 104 including three integrated generators 1102.FIG. 12 depicts an integrated generator 1102—module 104 example, wherethe nozzle may include PM turbine blades/rotor and exterior stator. FIG.13 depicts an array with storage 1300, including a pressure vessel 1302,fluid turbine 1304, fluid containment 1308, vortex tube 1310, flowchamber 1312, and turbine compressors 1314. FIG. 14 depicts a module ina triangular superstructure 104. FIG. 15 shows details the majorcomponents of an example nozzle 104, including the inlet screen 1502,inlet 1504, rotor 1508, transmission/generator 1510, supports 1512,control and management 1514, diffuser 1518, and exit screen 1520. FIG.16 shows two nozzles 104 in a serial arrangement 1602. FIG. 17 depictsan embodiment of a front and side elevation of a hexagonal nozzle 1700.FIG. 18 shows an example of a nozzle with circular throat and polygonalexit 1800. In this example, a nozzle with a circular throat mayinterpolate from 1/r curvature at the throat to 0 curvature at thepolygonal exit. In embodiments, intervening slice polygons may beReuleaux polygons. FIG. 19 shows and example of two nozzles 104 nestedtogether 1900, where splitting the rate of constriction between the twonozzles and nesting the smaller nozzle into the larger may increase theacceleration. FIG. 20 depicts a front view of a superstructure connector2002A and a side view of a superstructure connector 2002B. FIG. 21depicts a horizontal axis wind turbine generator arrangement 2100 withmodule protection screen mounts. FIG. 22 depicts a superstructure andmodule arrangement 2200 for hexagonal modules.

The module may be an important aspect of the invention, where a modulemay be an integrated element that is inserted into the array as a plugand play component. The module may be comprised of structuralcomponents, nozzle fascia, rotor, generator, transmission, powermanagement components, and the like. A module may be assembled aselements that fit separately onto a given superstructure cell. Themodule may have at least one automated locking/unlocking mechanism thatmay attach said module to both the superstructure and its neighbormodules. This may allow single modules to be removed and replaced atneed without effecting the operation or structural integrity of thearray.

In embodiments, the module may have at least one structural componentthat provides support for the main nozzle surface, including support andprotection for the power components. The structural components mayconstitute the main load- and pressure-bearing components of the array.Additionally they may include bundled power management and transfercomponents that connect into the main power conduit array.

In embodiments, an inertial rotor may manipulate rotational momentum toprovide variable rotational inertia by way of a variable radiusweighting system, where the rotor blades and hub may be comprised of asingle or plurality of staged chambers. In addition, a weighted materialmay be allowed to move based on centripetal motion toward the outerradius. This may be executed with a weighted material that may becontrolled in its balance under rotation. In the case of a fluid, thefluid may be allowed to cycle through a series of chambers therebycreating a more stable inertial rotation and energy output. Thisinertial rotor may also be executed by way of weights and flexiblestructures, such as springs, memory plastic, and the like, where theflexible structure and weight may be slotted into a single internalchamber in the rotor blades. As rotation and centripetal force increasethe weight may extend the flexible structure to the tip of the rotor andthereby change the inertia of the rotor to a more optimal profile forthe rotor's use. Weights or fluids may also be controlled by way ofactuators. In embodiments, the weighted material may be maintained at anextended position during certain conditions, such as when fluid forcesare falling off, when fluid forces are leveled off, when fluid forcesare at a maximum, and the like, where the extended position may be amaximal rotation position. In embodiments, the present invention mayprovide an array of nozzles adapted to generate electrical power fromthe flow of air. A rotor may be configured to operate within a windpower generating turbine, where the rotor may be configured to havevarying amounts of inertia, such as the rotor including a blade on aspring to provide varying inertia at different rotation speeds, therotor including a fluid component internal to a blade to providevariable inertia, and the like.

In embodiments, the nozzle portion of the module may be important inpower production. Nozzle types for manipulating the fluid flow mayinclude solid body w/ single fascia, solid body w/ plurality of fascia,partially open body geometry, and the like. There may be differentiatingcharacteristics to the underlying geometry of the nozzle. To optimizeplane use a quadric surface geometry may be utilized where the inlet ofthe nozzle is formed by the truncation of a radial or radial/ellipticalfunction at a polygonal boundary. This may allow the nozzle to cover apolygonal intake area with variable intake curvature while having aneffective momentum focusing circular structure and expanding to aclosely similar polygonal outlet area. The ability to cover anon-circular, for example a square inlet area, may yield a moreefficient use of the fluid plane, and the quadric geometry may maximizefascia separation and minimize overpressure relative to the throat.Additionally, the complexity of the surface geometry may be extended byapplication of quadric or radial structures to the underlying geometry.

A second characteristic may be the radial function used to determine thecurvature of the constrictive region conforms. The optimal curvature inthe prior art for a radial nozzle may be an arc section from a circle,such as between 1.8 to 2d, where d is the diameter of the throat. Suchcurvature may engender the loss of a large portion of the mass availableat the intake area.

In embodiments, different types of single arc and multi-arc curvaturesmay be used depending on the level of nozzle constriction, such as asingle arc radial or elliptical curvature used for exclusively lowconstriction rates, a single arc intersection of two radial functionsused at low or medium rates, a single arc execution based on an arcproportion determined by the vector interpolation of momentumdistribution described in the method section of this invention, multiarc and single-body or multi-body fascia for higher constriction rates,and the like. This curvature may also vary depending on its angularposition relative to bounding polygon and the center of the throat.

In embodiments, the divergent geometry in configurations of the currentinvention may be predicated on a ratio of rate of constriction to intaketo divergent section that results in a volumetric ratio function of theconvergent volume to the divergent volume wherein the volumetric ratioincreases with the rate of constriction. As an example, a 2×constriction may require a volumetric ratio in excess of 1:7, whichgiven the parameters described in above with regard to constriction mayresult in a less than 4 degree divergent angle. Additionally a variablenozzle may provide a constriction rate of the nozzle dynamicallyadjusted to the flow velocity to maintain velocity within the module ata given rated speed. This may allow the reduction of variability in thewind resource and allow the array to output at a given ratingconsistently.

In embodiments, the array superstructure and array installation may beprovided, where the array superstructure may be comprised of powertransfer and management and control components, module structuralsupport elements, the array support structure, and the like. Powertransfer components may be bundled into the modular structural supportcolumnar elements extending from the top to the base of the array andallowing the module power systems to transfer power with a minimumnumber of connections and resistance. The superstructure may be eithercentralized, such as with a mast and boom structure, or distributed,such as with multiple columnar supports.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includenetworked or distributed power control and transfer. The power controlmay optimize the power production within a plurality of nozzles and maymonitor power production for performance, maintenance, replacement, andthe like. The power control may dynamically manage load requirements fora plurality of nozzles, such as when the management is local, global,and the like. The power control may optimize performance through use ofneural networks, genetic algorithms, fuzzy algorithms, probabilisticpredictive-corrective feedback loops, and the like, to maximize outputand minimize losses. The power control may use a dedicatedcommunications system, routing system, distributed communicationssystem, and the like, to control individual elements within a pluralityof nozzles. The power control may utilize digital electronics, analogelectronics, an electronics chip, electronics logic gates, centralizedprocessing, parallel processing, distributed processing, be hard-wired,wireless, and the like. The power transfer may be integrated intostructural components, external to structural components, and the like.The power transfer may include topography that may minimize resistancelosses, such as with a branch-trunk network structure, a directgenerator-main trunk connection structure, and the like. FIG. 23 depictsa space frame for a square array in two different configurations 2302Aand 2302B. FIG. 24 depicts nozzle polygons with different entranceshapes with embedded structural members 2402A and 2402B, where the viewto the left shows a larger structural member embedded, and the view tothe right shows a smaller structural member embedded. FIG. 25 shows apower transfer arrangement 2502 in a square array showing the powertransfer structure with nozzles in place. This may depict an example ofa modular implementation where the horizontal structural member isembedded in the module and then locks into the columnar component toform the space frame. Other embodiments of this may include a clamshellapproach, direct assembly, and the like. FIG. 25 also shows a transferjoint with 35 kV main columnar cable 2504 connection, 25 kV generatorcable connection 2508, and connector plates 2510.

In embodiments, the superstructure configuration may be based on aparticular array implementation. Array implementation may follow anynumber of geometries based on module geometry, such as hexagonal,rectangular, triangular, trapezoidal, and the like, where array geometrymay not be dependent on module geometry. Array rows may additionally bemounted individually to allow individual row response to wind direction.These rows may be mounted on individual bearings, or the like, of thetypes described herein, or may be mounted centrally to a column wherethe outer fascia of the column and the inner fascia of the row may bemade up of the materials as described herein with reference to amaterial properties bearing. In such cases each row may be fitted withmechanical or flow based orientation mechanisms. Each array layer mayadditionally be executed with power management suited to the conditionsat array height, to increase overall output, to stabilize said outputbased on variation of power curve and dynamic loading as a function ofincreased velocity w/increased height, and the like. In addition, thesupport structure may be executed as either a central column or a seriesof columns. In the case of a series of columns, a number of machineplacement configurations may be used to maximize land use vs.installation output. For instance, a checkerboard or filled matrixconfiguration may be preferred wherein the foundation pilings are sharedbetween arrays at each intersection of the grid to optimize the yield toinstallation cost ratio.

In association with the installation, energy storage may be provided.Due to the variability of the resource it may be desirable to have acost-effective method of energy storage for a wind energy machine.Compressed air or pumped hydro storage or batteries or other facilitiesfor storage as are known in the art may be a cost effective way to storewind-produced energy wherein the energy produced by the array may beused to compress air or pump water up a gravity gradient. The storedenergy may then be used to power a turbine that produces energy basedupon grid demand not wind variability. A major problem with some storagesolutions is efficiency relative to cost. In the case of hydro theenergy storage requires a large facility and availability of water toaffect storage. For this reason compressed air may present a moregenerally applicable solution with fewer requirements in terms of spaceand construction. For instance, compressed air and vortex tubes may beused to create a density based closed loop flow system from which energycan be gathered, where vortex tubes can be used to separate flows intothe energetic and non-energetic components with an input of compressedair. Depending on the pressure of compressed air, temperature outputsbetween the hot and cold outputs of the vortex tube can be substantial,on the order of 100 C or more. As in a basic engine schematic, theseoutputs may be used in a closed loop system to create a hot and coldsink wherein the rate of flow may be determined by the temperaturedifferential between the sinks. While the energy contained in the rawflow is still inefficient with regard to amount of energy used tocompress the source gas, the introduction of optimizedconvergent/divergent (C/D) nozzles may provide a way to artificiallyincrease the amount of kinetic energy present at the point of conversionin the closed loop flow and thereby the amount of power recovered fromthe storage process.

In its simplest form, the storage/recovery device may include methods ofpressurizing the preferred medium, a pressure vessel for storage of thecompressed medium, a secondary external pressure vessel to recapturethermal energy released by compression with a method of controlling theflow to the turbine, a controlled valve to release the pressurizedmedium in the primary vessel based upon grid demand, at least one vortextube, a flow chamber, a facility to channel or transfer thermalproperties of the hot and cold streams into the flow chamber, aplurality of embedded nozzles within the flow chamber to increaseproportion of kinetic energy in the flow, a facility to control andmanage the power derived from both pressure systems, a facility togather all resultant KE and transfer the power to the grid, and thelike. The baseline KE and thermal energy that drives the system may becaptured through use of additional turbines such as a steam turbinederiving steam pressure and flow from heat given off by the pressurevessel during the air compression phase or KE turbine capture of theenergy of the fluid flow used to drive the closed loop system.

In embodiments, the present invention may include a plurality of processand functional components, such as orienting the array, a nozzle foraccelerating the air into the array element, a rotor motor that convertsthe kinetic fluid energy into mechanical energy, a gear box fortranslating the mechanical energy into usable rates or controlling theload applied to a facility for KE conversion allowing the energyconversion process to operate at in an optimal range, a generator toconvert the mechanical energy into electrical energy, energy storage, afacility for converting or conditioning the energy produced into adesired form, a substation and grid interface, fuel cell loading, andthe like. In embodiments, storage of energy may be taken from after thegenerator in the form of electrical energy, or before the generator inthe form of mechanical energy such as described herein. The array may beused in a direct energy transfer system, such as for pumping water,milling, pumping oil, pressurization, gas pressurization, hydrogenseparation, fuel cell loading, and the like. Mechanically, the presentinvention may include a plurality of components, such as the modulesthemselves, arrays of modules, arrays and arrangement of arrays, thesuperstructure, bearings, and the like.

In embodiments, the module or array may be provided with a way to orientitself relative to the fluid flow. For instance, a tail may be providedto self orient the structure, such as a tail placed on a rotatingsupport axis that spins the module or array to the wind's direction, orthe structure of the nozzle or the array may be constructed in such away to engender more orienting properties. There may also be otherconfiguration features that contribute to orientation, such as throughside cladding shape, providing different orientations at differentlevels, allowing different levels or modules or array segments to orientindependently, and the like.

In embodiments, the nozzle's configuration may provide an importantelement of the invention, such as a 2.75 constriction nozzle producing a6 to 7.5× power increase, and the like. Mass flow rate may be affectedby a number of parameters, such as rate of constriction, includingintake geometry and diffuser geometries being very sensitive to rate ofconstriction—as you move from 2 to 2.75, effects may become much moresensitive to things like the intake angle; past simple geometries,second order equations—may become very complex, where more complexgeometries and surfacing may become an effect; and the like. Inembodiments, a rate of constriction of 2.75 may be a good value, wherethe relationship of rate of constriction, curvature, length of diffuser,intake, etc. may be sufficient to achieve a large power increase withoutrelying on a complex geometry. With a constriction rate below 2 timesthe realized power increases might not be sufficient to provide anadvantage against HAWT systems with regard to a comparison of swept areaused by the whole machine and the relationship between cost and yield.Variable throat constriction may be a factor, with the ability to varythe throat. Temperature may be a factor, where heating the air or othermethods of creating additional sparsity rearward of the nozzle maycreate an improved flow, and may also be effective in a storage system.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may include aconstriction. For instance, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2and where the length of the diffuser is more than five times the lengthof the intake, and where the ratio of the diffuser length to the intakelength may be about 7:1. In embodiments, the constriction ratio of thediameter of the throat to the diameter of the intake may be more than 2and where the nozzle is used in an array of nozzles, or as an individualnozzle. In another instance, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2.5and where the length of the diffuser is more than five times the lengthof the intake, and where the ratio of the diffuser length to the intakelength may be about 9:1. In another instance, the nozzle may include aconstriction ratio of the diameter of the throat to the diameter of theintake of about 2.75 and where the length of the diffuser is more thanfive times the length of the intake, and where the ratio of the diffuserlength to the intake length may be about 11:1. In another instance, thenozzle may include a constriction ratio of the diameter of the throat tothe diameter of the intake of more than about 1.5 and where the lengthof the diffuser is more than five times the length of the intake. Inembodiments, the nozzle may include a converging intake and a divergingdiffuser, where the length of the diffuser may be longer than theintake, such as more than five times the length of the intake. Inembodiments, a nozzle may be adapted for use in a turbine for generationof power from ambient movement of air, where the nozzle may include anintake and a diffuser and where the length of the diffuser is longerthan the intake, such as more than five times the length of the intake.

Nozzle intake geometry may also play a key role in the presentinvention, such as in the leading edge geometry, curvature, length ofintake, exit geometry, and the like. The curvature of the intake may beimportant, such as when the average angle is greater than 45 degrees ina two times constrictor, then you might get a power loss. Once you go upto a 2.5 rate of constriction, then you may become much more sensitiveto curvature and length of intake. Length of the intake may beimportant, such as in the time that the gradient has to act on the flow.If intake length exceeds the throat by a significant factor, there maybe loss. Once intake length is less than the throat length, thensuddenly you may see the actual predicted velocities at the throat. Notethat if elastic collisions are assumed, momentum may deflect from theleading edge. It may not conform to that, nor to a classic boundarylayer problem. The effect of momentum deflection may be greater thananticipated by a momentum diffusion layer analysis. There may be somekinetic energy exchange with the wall that slowly turns with the intake.Looking at sparsity and density of molecules and delta of momentum basedon probabilistic movement of molecules in the sparse direction may beprovided. The lower rate of constriction, the shorter the intake lengthmay have to be. With an initial sparse gradient, if there is a properintake angle that allows momentum to be directed toward the throat, adensity increase may be experienced in the region of the intake. Whenthere is an incorrect intake geometry at a higher rate of constriction,a toroidal bleed-over on the leading edge may result in mass loss to theexterior of the nozzle.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, such as optimized for leadingedge geometry, for curvature, and the like. The leading edge of thenozzle may be optimized based on the angle of incidence to the directionof the flow, where momentum vectors derived from the leading edge maygenerally clear the throat of the nozzle. In embodiments, the intakeleading edge may have an angle of incidence of no more than 1.1*0.5*θ,where tan θ=(0.5(D_(I)−D_(t))+D_(t))/I₁, and where D_(t) is the nozzlediameter at the intake, D_(t) is the diameter of the throat, and I₁ isthe intake length. In embodiments, the present invention may provide anozzle adapted for use in a wind power generating turbine, wherein thenozzle is optimized based on intake length, leading edge shape, diffuserlength, and the like. In an example, for a nozzle where the area at thethroat is ½ the area of the intake and the intake length is ½ thediameter of the throat, the maximum incidence angle at the leading edgemay be 47 degrees. In embodiments, the optimal range may fall between 41and 37 degrees for 2 times constriction for this set of parameters. Theintake may conform to an elliptical, radial arc, a combination of thetwo, a combination of a plurality of elliptical or radial arcs from theleading edge to the throat, and the like. In embodiments, the nozzle maybe optimized based on an intake length to divergent length ratio wherethe intake length may be equal to or less than the diameter of thethroat.

In embodiments, the initial intake momentum vector may be depictedgraphically. FIG. 26 shows an diagram depicting an initial intakemomentum vector 2600, which may be related to the formula for derivingthe minimum leading edge angle. In the diagram, the incident path andincident momentum vector are shown relative to the intake curvature, theincident wall, and the opposite throat wall.

In embodiments, the design of the intake geometry may result in anon-perfect angle with relatively short diffuser. A 4× power increasemay result with a 45 degree intake angle, as long as there is curvature,where curvature spreads the force acting against the flow. A basicnon-symmetric catenoid (rotated hyperbolic function) may be used. Toachieve an array you may artificially truncate the catenoid (taking afunnel/catenoid) and truncating with a hexagon, square, triangle, orother polygon. In using a hexagon, there may be more exterior angularlatitude, but straight corners may have to be more curved. Surfacing maybe a factor, where there may be small vortex generators on leading edgesor over the entire nozzle surface, such as square vortex generators,golf ball dimples, or any surface that creates a thicker displacementlayer, but relates to the boundary layer better. In embodiments, thepresent invention may provide a nozzle adapted for use in a wind powergenerating turbine. The nozzle may include a diffuser, the cross-sectionof which may have substantially linear sides from throat to exit. Inembodiments, the exit angle of the diffuser may be less than about fourdegrees. The nozzle may have a facility to generate a voracity or swirleffect proximal to the exit of the diffuser, such as where the diffuserincludes a vane to facilitate the effect. In embodiments, the nozzle mayhave a diffuser, such as a diffuser with a polygonal exit shape, asquare exit shape, having symmetric polygonal walls, having symmetricpolygonal walls that are truncated, and the like.

In embodiments, low cost materials for nozzles may be a factor, where ifthere's an efficient pass through, the whole thing orients itself (actslike a big tail on a kite). Once you break into arrays and optimize, youmay not need materials such as carbon fiber, eGlass, and the like, butvery low-cost, lightweight materials may be used, especially at the topof the superstructure/array, such as a polycarbonate thermofoam, and thelike. A combination of inexpensive and expensive materials may also beused wherein the mechanical properties of a fiber in combination with aclosed or open cell foam may result in an overall cost reduction. Inembodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array mayinclude nozzles made with polycarbonate thermofoam, polymer, afiber/resin composite, a syntactic foam, a closed cell foam, an opencell foam, with gelcoat, and the like. In embodiments, the presentinvention may provide a nozzle adapted for use in a wind powergenerating turbine. The nozzle may include at least one of a pluralityof mass produced components. The components may be manufactured throughrotomolding, injection molding, scrimp molding, thermoforming, lay-up,vacuum molding, filament winding, and the like. The materials used inmanufacturing the components may include acrylonitrile butadiene styrene(ABS), polycarbonates (PC), polyamides (PA), polybutylene terephthalate(PBT), polyethylene terephthalate (PET), polyphenylene oxide (PPO),polysulphone (PSU), polyetherketone (PEK), polyetheretherketone (PEEK),polyimides, polyethylene,polypropylene, polystyrene, polyvinyl chloride,polymethyl methacrylate, polyethylene terephthalate, and the like. Thematerials used in manufacturing the components may include at least oneof acrylic, aramid, twaron, Kevlar, technora, nomex, carbon, tenax,microfiber, nylon, olefin, polyester, polyethylene, dyneema, spectra,rayon, tencel, vinalon, zylon, asbestos, basalt, mineral wool, glasswool, syntatic foams, carbon foam, polyurethane foams, polystyrenefoams, metal foams, and the like. The components may be designed toenhance the structural properties of the nozzle to provide reduced costof material, reduced weight of material used, minimized assembly time,minimized transport costs, and the like.

In embodiments, drill-throughs may be a factor, where a drill may gothrough from the outside to increase the flow from an ambient outsideair, or perform vaning with drill-through to introduce the ambient airand change swirl. In embodiments, the present invention may provide anozzle adapted for use in a wind power generating turbine, where thenozzle may include a through-hole to facilitate air flow.

In embodiments, more complex intake geometries may be a factor, such ascombinations of geometries, truncating a catenoid with a polygonalshape, taking a quadric function and applying it on an ellipse to thesurface creating aerodynamic shapes that channel well (e.g., sharkscales, single or multi-layer scalloping, whale fin, and the like),extending quadric truncation onto the surface of the nozzle spreadingthe momentum from off of the leading edges and bringing in the intakestream into a less oppositional mode, a series of linearly ororthogonally concave curvatures onto a convex shape, applying to thewalls at a larger scale, vortex generators within the nozzle itself(e.g., squares, dimples, vortex film, and the like), forward wedging tochannel the flow toward the throat, concave and convex curvature, splitdiffuser in half rearward of the throat, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may have a leadingedge and an intake curvature between the leading edge and a throat ofthe nozzle, where the leading edge and intake curvature of the nozzlemay be adapted to focus momentum vectors of air particles in the intakeregion to facilitate air flow within the nozzle. In embodiments, thenozzle may have a leading edge and an intake surface with an intakecurvature between the leading edge and a throat of the nozzle where theleading edge and intake curvature of the nozzle are optimized based onthe predicted gradient of air particles within the nozzle, the predictedenergy transfer of air particles in interaction with the intake surfaceof the nozzle, the predicted focus of momentum vectors of air particleswithin the nozzle, and the like. The nozzle may have a leading edge andan intake length between the leading edge and a throat of the nozzle,where the intake length of the nozzle may be less than the diameter ofthe throat of the nozzle, such as by two times. In embodiments, theintake length may be less than the diameter of the throat, betweenone-half and about equal to the diameter of the throat, and the like.The geometry of the nozzle may be adapted based on calculation of theprobability of movement of air molecules from dense to sparse regionswithin the nozzle. The surface of the nozzle may include a vortexgenerator. The nozzle may be configured with surface shaping to optimizeflow from the leading edge, such as based on quadric truncation of anellipse, multiple quadric functions similar to an n-iteration fractal,shark scale shape, scallop scale shape, whale fin shape, and the like.

In embodiments, nozzles may be in series, such as nesting nozzlesrearward of the throat, where the one in the throat may come very closeto a theoretical level of increase, and the outside one may get 90% ofits theoretical level of increase. In embodiments, the nozzle module maybe integrated as one piece, such as making the blades of the rotor ofthe turbine an integrated component. Other less optimal forms may alsobe used and combined into an array such as super-venturi's, wide-anglediffusers, two dimensional nozzles, flat wall nozzles, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may have an intakegeometry configured to optimize airflow based on momentum vectors in theintake region, where the momentum vectors may derive from interactionwith the angle of the leading edge of the nozzle, the nozzle may beconfigured to generate momentum vectors that are directed to clear thethroat of the nozzle after interaction with the leading edge of thenozzle, and the like. The nozzle may be arranged in series with at leastone other nozzle. The nozzle may be formed with a constriction ratiobetween the intake diameter of the nozzle and the throat diameter of thenozzle, such as about 2.75, between 2 and 4, between 2.5 and 3.5, andthe like. In embodiments, the nozzle may include a constriction ratio ofthe diameter of the throat to the diameter of the intake of about 2 andwhere the length of the diffuser may be about seven times the length ofthe intake. In embodiments, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2.5and wherein the length of the diffuser is about nine times the length ofthe intake. The nozzle may be configured with the capability to vary thediameter of the throat. In embodiments, a facility may be provided formodifying air temperature or density in the environment of a nozzle toincrease flow through the nozzle, such as modifying air temperaturethrough heating air in the proximity of the outtake of the nozzle.

In embodiments, diffuser geometries may be a factor, such as exit angle,length of diffuser, splitting the diffuser in half, in quarters, and thelike, increasing the diffuser efficiency, the diffuser shape, the radialswirl, and the like. For instance, as the rate of constrictionincreases, the optimum diffuser may become longer, and longer as arelative ratio to the intake, such as at 2 there might be a 1:7 optimalratio of diffuser length to intake length, at 2.5 there might be a 1:9optimal ratio, and the like. The diffuser shape may be a curve, takenstraight to the outlet, convert the radial function to a polygonalfunction, use long or wide angle diffusers, use optimized nozzles forwind conditions with long diffusers, and the like. The radial swirl maycreate low-level swirl or higher rates of vorticity in the exit regionor rearward of the diffuser, where curved vaning may create an exterior,radial motion of the gas as it exits, which may create an additionallayer of sparsity inside the diffuser. In addition, the swirl may becreated using ambient air, vaning could be used with drill-through tointroduce the ambient air and increase the swirl, and the like. Othermechanical methods of creating sparsity as described herein may beutilized, such as an inverse rotor attached to the main KE convertingrotor may be used with an optimized geometry and an arrayimplementation. Such methods of increasing sparsity might allow the useof a non-optimized geometry that could have a positive effect on thecost parameters of the machine.

In embodiments, the relationship of intake geometry and diffusergeometries may changed based on the rate of constriction. To create ahigh mass throughput, as you increase rate of constriction, the intakeand diffuser geometries may become far more important.

In embodiments, the rotor parameters may be important in the currentinvention, such as the shape of the blade and surfacing (which maycreate vortices both on the upper and lower surface of the blade). Aplurality of blade shapes may be employed, such as using vortexgeneration on the lower edge (which may add to the lift of the blade),lower angle for more power (but if the angle goes to zero, there may beno lift, so some low number may be good, such as a mean angle of fourdegrees), minimize the drag effect on the top of the blade due to theboundary layer effect (which may be hard to control if the direction thegas is coming from is unknown, so creating different kinds of bladeshapes that minimize boundary layer separation above the blade may bevaluable), drill throughs to address the boundary layer, making blades ainexpensively as possible, and the like. For example, the rotor may betwo meters long, formed of thermoplastic, could be hollow, and operatewith a basic swept-twist airfoil. Adjustable pitch may be used toincrease blade efficiency at higher velocities by adjusting to a lowerpitch angle.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. A rotor maybe configured to operate within a wind power generating turbine wherethe rotor includes a complex topography vortex generation facility onthe blade, such as a vortex generation facility on the lower surface ofa blade, such as a vortex generation facility on the upper surface of ablade, vortex generation facility includes providing a dimple on thesurface of the blade, a shark scale topography, and the like. A rotormay be configured to operate within a wind power generating turbine,where the rotor may include a low angle relative to the plane ofrotation of the rotor, such as the angle being less than approximatelyfour degrees.

In embodiments, the rotor may be a variable inertia rotor, where if themass of the rotor is centralized around the hub, there is less inertiato start the rotor. In embodiments, there may be a facility forsmoothing the mechanical energy output of the rotor, the power capturemay be extended as the wind drops off where there may be more powerduring drop off as the weight is placed out on the edge, change thedynamics of rotor between low speed state and high speed state therebyholding it longer, and the like. In embodiments, the configuration mayshift the mass to the outward part as it gets as rotation rateincreases, such as by attaching a memory plastic spring, by using arubber elastic actuator, by using a metal spring, by spring loadedactuation, by actuation with a coil with a current going through it, bya fluid, by a mechanical actuator, by enlarging the rotor, throughcentripetal motion, and the like. By utilizing a spring, narrowing atlower speeds may be avoided, which may happen on drop-down of the wind.A start weight may also be used at the center, then move out and holdpeak power production with inertial at high speed and as the wind drops.In embodiments, a mass on a spring may be used to move the inertia outto the edge of the rotor, such as by putting a flat or round pipe up thecentral axis of the rotor, putting a mass on the spring, slotting it,and letting it get to the end, where as it slows down, the spring pullsit back in, or the spring releases a weight, and the like.

In embodiments, the rotor may utilize a variable blade, such as startingout with six blades, and then activate an actuator for pressure-basedswitch allowing some blades to collapse in order to reduce the totalnumber of active blades. For example, this may be done with any primemultiple, such as eight dropping to four and then dropping to two, ortwelve drops to six which drops to three, and so on. In this instance,the prime number blade may have the most structure, with the secondaryand tertiary with less structure, such as being made from thermoformsthat slot into the hub, and collapse as the wind speed increases. Inembodiments, energy capture at a given fluid velocity might go from 12%to 30% with the right blade number, so if one wants to get a good powercurve over a range, one might get the right blade configuration andmaximize over a whole range of velocities. This may translate into asignificant increase in annual yield. For instance, what is consideredlower speeds may be 60-70% of maximum (distribution) at any wind site.Today's systems often ignore the low wind, because one gets so much morepower out of the high wind areas. Most of East Coast on-land and closeurban sites (other than directly on shore—are class 3 or 4 sites. Theentire Southeast is a Class 1 site. Where the wind works now (Class 5),there are other problems, because of distance from major urban centers.Thus, setting up a system that works at low wind and still works at highwind is very effective.

In embodiments, the structural configuration of the module may beimportant to the present invention. For instance, the module may be anintegrated assembly that is put together separately with superstructureelements connected into the module, and then everything is connectedtogether. In embodiments, the structure could be a hexagonal, square,triangular, and the like arrangement that components are placed into, abasic geodesic structure and put module components into, and the like.There may be a need for actuators in the superstructure itself, so thatthe cover can be opened and closed. In embodiments one may build columns(power transfer columns) and fill in the space with modules. Eachsuperstructure element of a module may click into a bus that clicks intothe main one (as opposed to providing individual lines. If donemodularly, then one component could be popped out, and another poppedin, thereby providing a complete modular implementation, with a runningstock of replacement modules. In embodiments, the modules could be onsleds with their own way of getting down to the ground or may beinstalled by way of a built-in installation platform. There could alsobe a Pseudo-modular implementation, by making the super structure andinserting elements of the module individually. Components could beassembled in installation versus off-site. One could make modules inpieces, such as a clamshell top piece and a clamshell exit piece for thenozzle, where one puts the generator onto super structure first. Guidepoles or a form of guided crane may be utilized for removal of parts forreplacement. There may be a slot in the superstructure, such as forwardand rearward on the superstructure with slotting poles such that modulesare installed onto the slotting poles. Modules may be manufacturedon-site, such as manufacturing in a tractor-trailer, where for instance,nozzles may be made on site. Once the process is automated, thelikelihood of human error may be lower.

In embodiments, there may be wildlife protection/anti-fouling systemssuch as screens on the same pole as used on the superstructure, wherebirds and bats may pose a problem. In embodiments, bugs may not be asignificant issue, but there may be self-cleaning surfaces utilized,such as certain plants, like lotus leaves, where viscosity of theinherent molecules may not bond to the surface. Modularity may allowslotting out the screens and cleaning them. In embodiments, the presentinvention may provide a nozzle or array of nozzles adapted for use in awind power generating turbine, where the nozzle may be adapted forextreme conditions, such as earthquakes, high wind, ice, and the like.The adaption for extreme conditions may include mechanisms to allow thenozzle to survive earthquakes, where the mechanism may be a fluidfoundation, a gyroscopic mechanism, a pintle mechanism, a frequencydamping mechanism, and the like. The adaption for extreme conditions mayinclude mechanisms to allow survival of high winds, such as category 5winds. The adaption for extreme conditions may include mechanisms toallow for partial structural degradation of the nozzle. In addition, theadaption for extreme conditions may include mechanisms for deicing thenozzle. The nozzle may also be protected by a wildlife inhibitor, suchas a broadcasted sonic inhibitor, a mechanical screen, an olfactoryinhibitor, and the like.

In embodiments, arrays of nozzles and the arrangement of the arrays maybe an important aspect of the invention, where there may be advantagesin an arrayed configuration. For instance, as compared to monolithic, ifan efficient proportion is one to ten, then you may need much more powerto efficiently use the space required by a monolithic nozzle, and it maynot be stable without some structural components made out of expensiveaerodynamic materials. In certain embodiments, the distance needed toreestablish flow after the outlet of the turbine is approximately thedepth of about one array, and one may thus stack arrays behind eachother, such as in the checkerboard of FIG. 2 or in a co-mountedconfiguration.

In embodiments modules may be configured in the arrays to cover asignificant portion of the plane of the array. In embodiments the bestway to cover the plane may be to have the truncated catenoid geometry.If a comparison is made between an array and a conventional turbine, onemay start to see big differences, such as an array on platform comparedto a tall turbine. Additionally, the area of the array may not have tobe a fixed shape or size. For instance, the array could start at 30 mand go up to 90 m, or it can start lower. In embodiments, the presentinvention may provide an array of nozzles adapted to generate electricalpower from the flow of air, where the array may include nozzles ofvariable type at different height. For instance, some nozzles may belarger at greater heights than nozzles at lower heights, have lowerconstriction at greater heights than nozzles at lower heights, and thelike. The array doesn't have to have a circular structure, so it mightbe 115 m by 35 m, or alternately, it might cover a similar swept area ina similar of different proportion. In embodiments, more power may bederived, because there is more area at the higher wind speed. Anotheradvantage may be that in a traditional single large blade turbine theremay be different wind speeds at the top verses the bottom of the prop,and the difference may produce uneven stress loads and production atsome mean figure. In the current invention each row may get more thanthe rows at the bottom, with no stress load between the top and bottomrows. The top one or two rows, on their own, may gather more than theentire traditional turbine prop. The ability to manipulate how youhandle the area of the array is a major factor in generated power,footprint, and the absence of the need for custom building, and thecurrent invention may allow the custom design, generating energy basedon the power curve, wind distribution, and the like. In embodiments,with an array design, the configuration for an efficient, modular, spaceframe super structure may be re-used for many different sites.

In embodiments, array parameters may include the optimal number ofmodules, where the parameters may include tangential wind loads, icing,inertial components, cost of making the rotor, load bearing, poweryield, area covered, nozzle depth, tradeoff of height and depth, and thelike; the vertical starting point at which the array begins; thevertical point at which the array ends; the width of the array; depth ofthe array; shape of the modules, such as square, diamond, hexagon,triangle, rectangle, combined packing shapes of polygons, packingpolygons, and the like; shape of the array, such as square, diamond,triangular, trapezoid, shaped cladding (where something that bleeds thewind in the direction the nozzles bleeds the wind, with duplicateoutside coverage of the nozzles, and/or extending of the cladding);variability of the modules, such as sizes and shapes; bearings, such asbetween array rows to orient independently or for the whole array, amagnetic bearing, a wind bearing, bearings for rows of arrays, and thelike; uniformity, such as outside modules smaller than inner modules orthe inverse, impact on structural bearing of the array, impact on theelectrical distribution, and the like; load bearing properties, such asmanaging load across the array; the ability for a series configuration,such as placed end-to-end, in a grid, based on a fraction of the exitspeed, and the like; turbulent mixing over the outer part of the module,such as with vortex generators, axial stream tubes, like drill-throughs,trailing edge on airfoil with vortex generator, optimizing the trailingair mix; combined outer shape of the array; the superstructure;installation properties of the individual array; installation propertiesof the wind farm, such as dimensions relative to each other;arrangements of the arrays; and the like. In embodiments, laying out thearrays into a wind farm configuration may entail a plurality of designparameters, such as the minimum optimal dimensions across the array, thefront array numbers and dimensions verses the back, where the arrays areplaced in the wind farm, whether the wind farm can be placed near urbanspaces, on top of a hot spot, close to transmission line, and the like.

In embodiments, the super structure parameters may present importantaspects to the present invention, such as modularity; applying spaceframes to the superstructure of the array; integrating with the shape ofa given module; integrating with the power structure; load bearingsupports, such as relative to the length of the modules, a need forlateral support, square shapes bearing less than a diamond shape, andthe like; shaped space frame, such as cladding on the space frame,deciding which members need to be thick, placement of lateral support,and the like; structural space frame as an electrical conduit;transferring power through the super structure, such asattaching/conducting power, placement of busses, placement ofconnectors, need for main bus columns, attachment of modules within thestructure to the main bus column, running wire from each one to acentral bus to transfer to the grid in one big cable, minimizingresistance to help allow efficient distribution of energy, minimizingcomplexity and cost of installation and maintenance, and the like; pipeshapes; superstructure weight distribution; and the like. Inembodiments, the present invention may provide a structural array forgenerating electrical power from the flow of air, wherein the structuralarray may be a composite space frame wind producing array superstructure. The space frame may be made of composite or alloy materials.The space frame may include variable profile structural members,variable solidity members, variable members, fixed members, and thelike. The space frame may also include properties to enhance structuralproperties, material use, material cost, material weight, and the like.

In embodiments, the electrical system may present important aspects tothe present invention, such as electrical distribution within thesuperstructure; dynamic voltage regulation; high voltage handling; loadregulation; load management/load parsing, such as a higher load on theupper end of the array, parsing the load on a single machine with anarray of turbines, and the like; load splitting; power/energy transfer,such as power conditioning of power from any array, network architectureto distribute load, managing a network, neural networks, substation,grid interface, and the like. In embodiments, the storage system maypresent important aspects to the present invention, such as whetherenergy to compress a fluid or gas, where energy diverts from the gridinto a compression system to say, run turbine compressors off of energy,a water vessel to use heat as you are compressing, blowing compressedair into vortex tube, radiators on bottom of circulating chamber, builda mini version of the wind in a circulation chamber, put turbines in theconfiguration to produce a very efficient storage system, making windflow based on hot and dense using nozzles to convert that helpsstabilize the output over an hour and then goes out to the grid,stabilize over an hour, use vortex tubes to create massive pressuredifferentials, and the like.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where anelectrical load management facility may be provided for managingvariable electrical load associated with different power generationcomponents of the array. Alternately, a mechanical load managementfacility may be provided for managing variable electrical loadassociated with different power generation components of the array.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may include power control. The power control may be networked ornon-networked. The networked power control may include power transfer,such as power transfer being integrated into the structural components,external to the structural components, including a network topographythat minimizes resistance losses utilizing at least one of a branch andtrunk network structure and direct generator-main trunk connectionstructure, and the like. The networked power control may optimize thepower production within the array and monitor power production of thearray for performance, maintenance, replacement, and the like. Thenetworked power control may dynamically manage load requirements for atleast one of a plurality of arrays. The networked power control may useoptimization methods such as neural networks, genetic algorithms, fuzzyalgorithms, probabilistic predictive-corrective feedback loops and thelike, to provide maximizing output, minimizing losses, and the like. Thenetworked power control may use a dedicated communications system, arouting system, distributed communications system, and the like, tocontrol individual network elements within at least one of a pluralityof arrays. The networked power control may utilize digital control.analog control, and the like, may utilize an electronics, electronicschip, electronics logic, and the like, use centralized or distributedprocessing, be hard-wired or wireless, including at least one of anelectronics chip and management algorithm, and the like.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may include power conversion elements, power management elements,and the like. The power conversion and management elements may beconnected to a power frequency converting mechanism, power conditioningmechanism, and the like, to prepare the power generated for storage,transmission, use, and the like, where the mechanism may be an LVDCconverter, HVAC converter, LVDC frequency converter, HVAC frequencyconverter, and the like. In embodiments, power management may be local,global, and the like. The power conversion and power management elementsmay utilize power diodes, thyristors, transistors, power MOSFETs, IGBTs,and the like. In embodiments, the power conversion and power managementelements may operate the array for fixed speed generation, operate thearray for variable speed generation, performed by electrical facilities,performed by mechanical facilities, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may convertkinetic energy from the wind into at least one of electrical andmechanical energy. In embodiments, the conversion may be made with aconversion mechanism including at least one of a DC direct driverotating machine, AC direct drive rotating machine, flywheel, generator,transmission/gearbox, synchronous singly-fed DC rotating machine,synchronous singly-fed AC rotating machine, asynchronous singly-fed DCmachine, asynchronous singly-fed AC machine, asynchronous doubly-fed DCmachine, asynchronous doubly-fed AC machine, induction singly-fed DCmachine, induction singly-fed AC machine, induction doubly-fed DCmachine, induction doubly-fed AC machine, MHD DC rotating machine, MHDAC rotating machine, Maglev DC rotating machine, Maglev AC rotatingmachine, low-speed DC rotating machine, low-speed AC rotating machine,medium speed DC rotating machine, medium speed AC rotating machine, highspeed DC rotating machine, high speed AC rotating machine, variablespeed DC rotating machine, variable speed AC rotating machine, fixedspeed DC rotating machine, fixed speed AC rotating machine, variablefrequency DC rotating machine, variable frequency AC rotating machine,fixed frequency DC rotating machine, fixed frequency AC rotatingmachine, squirrel cage DC rotating machine, squirrel cage AC rotatingmachine, permanent magnet DC rotating machine, permanent magnet ACrotating machine, self-excited DC rotating machine, self-excited ACrotating machine, superconductor DC or AC rotating machine,superconductor AC rotating machine, 1−n phase DC rotating machine, 1−nphase AC rotating machine, coreless DC rotating machine, coreless ACrotating machine, vibrational mechanism, and potential energy basedmechanisms. The conversion mechanism may also be controlled by at leastone of an electrical and mechanical power control management facility.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includespeed and load management facilities wherein the speed managementoptimizes the relationship of rotor speed, power conversion, andaerodynamic losses. The speed facilities may include electrical ormechanical mechanisms to operate the machine at variable or fixed speed.The load management facilities may include either electrical ormechanical management of the load applied to the rotor or generator.Electronic load management may be performed by means of powerelectronics. Mechanical load management may be performed by means of atransmission or gearbox or a geared, CVT, or applied field type.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includepower conversion management elements. The power conversion managementelements may be connected to at least one of a power frequencyconverting mechanism, power frequency conditioning mechanism, LVDC toHVAC converter, LVDC to HVAC frequency converter, and the like, toprepare the power generated for at least one of storage, transmission,and use. The power management may be local, global, and the like. Thepower management elements may utilize power electronics, such as a powerdiode, thyristor, transistor, power MOSFET, IGBT, and the like. Thepower management elements may operate the array for fixed speedgeneration, variable speed generation, and the like. In embodiments,power management may be performed by mechanical facilities.

In embodiments, detailed aspects of the nozzle configuration may beimportant to the present invention, where the differentiators betweencurrent technologies and the current invention may include polygonaltruncation of a figure of revolution to create the underlying geometry,leading edge (LE) geometry as constrained/determined by intake length,curvature, and LE angle relative to constriction, use of intake andconstriction parameters to determine diffuser geometry, and the like.

In embodiments, the current invention may use a particular nozzlegeometry to accelerate a flow under constriction to a high percentage ofits theoretical velocity increase. The nozzle may conform to the basicConverging-Diverging or DeLavel structure with the constriction rate ofthe convergent end serving to accelerate the incoming flow and thediverging to “re-expand” said flow. The nozzle geometry may be based ona molecular fluid dynamics theory that differs substantially from thecontinuum approach and is also dissimilar to numerical methods, such asLattice Boltzmann Method (LBM's) or Monte Carlo methods. The nozzlegeometry differentiators may include the basis geometry, specificgeometry with regard to LE characteristics and volumetric ratios, andsurface geometry.

In embodiments, plane use optimization may be achieved by way of a basisquadric surface geometry wherein the inlet and exit geometry of thenozzle is formed by an asymmetric (with regard to both axes) hyperboloidof revolution of one sheet truncated at an orthogonal regular orReuleaux polygonal boundary. The hyperboloid of revolution may beobtained by the use of an asymmetric catenary function or a closelysimilar combination of radial/elliptical or truncated radial/ellipticaland linear functions. In an adjusted catenary form the hyperboloid ofrevolution can be obtained with the following equations and conditions.For the intake mapping values the hyperbolic cosine function, y=a*cosh(x/a), can be used for the set of real numbers where x<0 and where ‘a’is determined as a function of desired rate of constriction and intakelength. For exit values, the set of real numbers where x>0, thefollowing formula is used, y=(a^(n)*cos h(x/a^(n)))−(a^(n)−a), where ndetermines the rate of divergence/increase from the initial (0, a)throat value for the y values of the function.

In embodiments, the polygonal truncation of the hyperboloid ofrevolution may allow the nozzle to cover a polygonal intake area withvariable intake curvature while having an effective momentum focusingcircular structure and expanding to a closely similar polygonal outletarea. The ability to cover a non-circular, for example a square inletarea, may immediately yield more efficient use of the fluid plane. Thepreferred polygons or combinations thereof are those that can be tightlypacked and provide a minimal surface area solution with regularpolygon/s used for complete plane coverage or Reuleaux polygon/s usedwhen a percentage of freestream flow through the given structure isdesired. Higher order regular polygons may also be used to allow apercentage of freestream flow.

With regard to the exit it can be formed either by truncation of theasymmetric catenoid or linear element or by interpolating the relativearc curvatures to from a value of 1/r_(t) at the throat (where r_(t) isthe radius of the throat) to 0 at the exit expanding therein to thedimensions of the entrance polygonal truncation. In the case of theReuleaux polygon the curvature of the arc segment forming the sides isused as the lower value. In the regular polygon and Reuleaux polygonexit cases the geometry is based on the figure of revolution but doesnot constitute a figure of revolution. Additionally, in the case where aportion of parallel exit is preferred this can be added as an extensionof the truncating polygon. In this regard, global (e.g. for the wholenozzles vs. a bounded area in the nozzle) rate of constriction andthereby the parameters of a regular truncating polygon is given by,

${r = {{Ai}/{At}}},{{{or}\mspace{14mu} r} = {{\frac{\left( {n/4} \right)s^{2}{\cot\left( {\pi/n} \right)}}{{\pi\left( {{.5}d_{t}} \right)}^{2}}\mspace{14mu}{or}\mspace{14mu} s} = {\frac{r\;{\pi\left( {{.5}d_{t}} \right)}^{2}}{\left( {n/4} \right){\cot\left( {\pi/n} \right)}}{.5}}}}$where n is # of sides, s is the side length, r is the rate ofconstriction, and d_(t) is the desired throat diameter.

The resultant geometry may be constrained by the following parameters inorder to insure high-mass flow through the nozzle. The initial angularLE value of the radial or catenary function for the curvature of theconstrictive region can be determined two dimensionally in its simplestform by using a radial arc approach and is given by the convergence of ifor the following equations,

$i = \frac{{.5}\left( {d_{I} - d_{t}} \right)}{{{1/\sin}\;\theta} - \left( {{{1/\sin}\;\theta^{2}} - 1} \right)^{.5}}$and$i = \frac{d_{t} - {{.5}\left( {d_{I} - d_{t}} \right)}}{\tan\;\theta}$

wherein:

θ=vector resulting from initial incident leading edge angle

i=intake length from leading edge to throat

d_(I)=diameter of intake

d_(t)=diameter of throat

Dependent on the value of y and the rate of constriction, this can be acatenary, radial, elliptical, or truncated radial, truncated elliptical,or combination thereof constrictive/convergent section.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. A nozzle may be adapted for usein a wind power generating turbine, where the maximal optimal curvatureof the nozzle intake may be determined two dimensionally in its simplestform, such as in the case of a radial arc, may be given by theconvergence at the initial angular leading edge, such as the value of ifor the following equations: i=(0.5(d_(I)−d_(t))/(1/sin θ−(1/sinθ²−1)*^(0.5)) and i=(d_(t)−0.5(d_(I)−d_(t))/(tan θ), where θ=vectorresulting from initial incident leading edge angle, i=intake length fromleading edge to throat, d_(I)=diameter of intake, and d_(t)=diameter ofthroat. This optimization may be applied two dimensionally or threedimensionally to a catenary, radial, elliptical, truncated radial,truncated elliptical, or the like function. In addition, a nozzle may beadapted for use in a wind power generating turbine, where the optimalcurvature of the nozzle intake may be greater than two times the throatdiameter.

The geometry of the i value convergence may be applied globally acrossthe intake derived from an i boundary maxima or at some lower boundary ivalue. It may also be applied locally with interpolated values, whereinthe truncation boundary's minima and maxima are solved separately andthen used with a weighted interpolation (matching the curvature of themaxima-minima interstitials) to determine the local i convergencerelative to varying intake lengths across the polygonal boundary. Whenapplied locally the resultant geometry does not conform to a normalfigure of revolution as in the divergent case above. An additionalconstraint herein is that the mean value for i be preferably equal to orless than the diameter of the nozzle throat. An additional constraint isto maximize the rate of curvature of the wall within the other geometricparameters and this can be inherently optimized by the precedingequations. In this regard the value of θ can be relaxed by a coefficientdefined by the following relationship: C_(r)=1+2((1/r)_(r)), wherein ris the rate of constriction. Thereby the relaxation coefficientapproaches a minimal value as the rate of constriction increases.

Extant “optimal” intake curvatures, researched under pressurizedconditions, indicate that the optimal curvature for a radial nozzle,regardless of rate of constriction, is an arc section from a circlebetween 1.8 to 2 d where d is the diameter of the throat. Research infurtherance of this invention has shown that such curvature engendersthe loss of a large portion of the mass available at the intake area.

With regard to the divergent portion of the nozzle an angular value fromthroat to exit may be used to determine the volumetric ratio of thedivergent length to convergent length. The constraint herein is that theangle of the divergent wall be no more than 5 degrees, with the anglerelative to rate of constriction preferred being described by thefollowing equation, ø=C_(d) (a+b+b^(5+a)) where a=1/r^(r), b=r^(1/r) andC_(d) is an adjustment coefficient related to intake length, wherein ris the rate of constriction. Therefore the divergent geometry in thecurrent invention is predicated on a ratio of rate of constriction tointake length to divergent length that results in convergent todivergent volumes wherein the volumetric ratio increases with the rateof constriction. It is this combination of specific LE geometry with avariable, rate of constriction and intake dependent,convergent-divergent volumetric ratio that enables high percentage massflows. Additionally the complexity of the surface geometry of the nozzlecan be increased by application of quadric or other complex structuresto the basis geometry. This may include small-scale structures used forflow enhancement or larger scale structures for structural or flowenhancement.

Said quadric functions can be bounded to create n-structure surfaces,e.g. scales or dimples, or can be applied globally across the surface asin corrugation or scalloping or rearward truncated scalloping, boundedby the initial truncating polygon. Scale and origin points of thequadric structures can be varied and the surfaces can be compound, withmultiple layers of quadric structures mapped against the precedinglayers' basis geometry. This allows the combination of various globaland local flow-enhancing elements to maximize the nozzle massthroughput. Additionally said quadric structures can have drill-throughsin either single layer or channel implementations to the near wallcharacteristics of the flow.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may include avariable wall profile, such as a wall profile utilizing linearscalloping. The nozzle may include complex wall topography, where thecomplex wall topography may maximize structural properties, minimizematerial use, minimize material weight, and the like. The complex walltopography may have a uniform circular profile, polygonal profile, andthe like. The complex wall topography may provide a variable profile,such as with linear scalloping, being generally radially curved, beinggenerally elliptically curved, and the like. The complex wall topographymay provide a variable density structure, uniform, variable, and thelike. In embodiments, the complex wall topography may provide nozzlecomponents that may be variably adapted to the lowest cost solution forlocal load bearing parameters within the nozzle. The complex walltopography may provide nozzle components that are made of rigidmaterials, flexible materials, and the like.

In embodiments, the performance characteristics may be provided. Anumber of single layer quadric truncated and non-truncated nozzles havebeen fabricated based on the above parameters. Nozzle constriction rateshave ranged from 2-4 with regard to the ratio of the intake to thethroat. In cases where the desired rate of constriction exceeds 4,single layer quadric geometries are insoluble as i tends to infinitywithin the constraint of the LE vector solution. In such casesmulti-layer and/or multi-body quadric structures are preferred. Nozzleswere fabricated in two throat size ranges 25 cm and 10 cm with theattendant geometric parameters deriving from the structural descriptionsabove.

As is well known in the art the Bernoulli equation describes thecontinuum pressure-velocity relationship of a fluid flowing through aconstriction wherein the rate of constriction results in an equal rateof acceleration for the mass in question as detailed by the change in KE(u) and internal energy (p). The majority of extant work in nozzleoptimization is therefore based on pressure measurements. There ishowever a substantial divergence in the prior art (Reid et al) betweenthe empirical measurement of volumetric mass flow and. pressureefficiency of nozzles. This indicates that, with regard nozzleefficiency, pressure might not be the most accurate variable. The massthroughput of a particular nozzle geometry is the variable of primaryimportance in categorizing efficiency. Mass flow efficiencycategorization of these nozzles derives from velocity and power data. Incomparing velocity results with power results, which are directlydependent on mass throughput, the nozzle performance can be accuratelyjudged by their close agreement. The velocity relationship relies on themass flow equation, Mdot=puA, where p equals density, such that, forgiven areas A₁ and A₂, Mdot_(a1)=p_(I)A₁u_(I), andMdot_(a2)=p_(t)A₂u_(t), and solving for u_(t) with Mdot and p valuesbeing the same for both in incompressible flow gives, u_(t)=u_(I)A₁/A₂or simply the u_(I) value is multiplied by constriction ratio of theintake to the throat thereby providing the theoretical velocity increasein u for a given constriction.

Mass loss to the exterior of the nozzle will therefore be apparent inthe velocity measurements based on the following, where the maximum massflow rate is Mdot_(max)=pu_(I)A₁ and, Mdot_(actual)=pu_(a)A₂, mass loss% at throat=u_(a)A₂/u_(I)A₁=Mdot_(actual) Mdot_(max) by which the massefficiency of the nozzle can be judged based on actual velocitymeasurements. With regard to power analysis, the power equation can bederived by combining the KE and mass flow equations wherein the Mdotterm is substituted for the mass term. Thereby the theoretical ratio ofpower at the intake and throat adjusted for area difference becomes,

$R_{{pt}\text{:}{pi}} = {\frac{\left( {A_{i}\left( {A_{t}/A_{i}} \right)} \right)*p*\left( {u_{i}{A_{i}/A_{t}}} \right)^{3}}{A_{i}{pu}_{i}^{3}} = {{\frac{A_{t}}{A_{I}}*\frac{u_{i}\overset{3}{A_{I}}}{A_{t}}*\frac{\overset{3}{1}}{u_{I}}} = \frac{\overset{2}{A_{I}}}{A_{t}}}}$And therefore,Pt=Pi*R _(pt:pi)

And the nozzle mass flow can be expressed as a function of power,Mdot_(actual)=P_(actual)/0.5 u_(actual) ² Where, u_(actual)=(0.5 A_(t)p/P_(actual))^(1/3) and given simultaneous measurement inside andoutside the nozzle, Mdot_(actual)/Mdot_(max)=(P_(actual)/0.5 u_(actual)²)/(P_(max)/0.5 u_(max) ²). Where, u_(max)=u_(I)A_(i)/A_(t)=(0.5A_(t)p/P_(max))^(1/3) and, P_(max)=P_(i)*(A_(i)/A_(t))². Thus the samemass loss rate can be determined as in the velocity case. For example anozzle with a constriction of 2 would yield a 2 times velocity increaseand a 4 times power increase. If the mean measured velocity increase is1.7, the mass flow efficiency would be approximately 0.85 of the maximalvalue. With regard to power this mass flow results in a power increaseof approximately 2.5. Conversely, a mean velocity increase of 1.85indicates a 0.94 value for mass flow which results in a 3.3 powermultiple.

With regard to the structural parameters described above optimum massflow performance range for this nozzle type is detailed in the followingtable:

Table of optimum parameters for structural variables with massthroughput and measurement ranges: V inc. r θ_(LE) C_(r) L_(i)/d_(t)L_(d)/L_(i) Ø_(D) Mdot % mean P inc. mean 2 31 0.5 >1, opt .5 >6 <2.92-1 1.8-2  3-4 2.75 27 0.12 >1, opt .8 >8 <1.5 .95-1  2.5-2.755.625-7.56  4 25 0.03 >1, opt ~1 >12 <1  .815-0.9 3.25-3.6 8.66-11.6

It was found that divergent length and function thereof is mainlydependent on intake length not throat diameter, as in prior art,although in higher rate constrictions these values are forced toapproach each other by geometric and curvature constraints. Variation ofthe intake length and the diffuser length but not the throat diameterresulted in little or no performance difference, providing the ratio ofL_(d)/L_(i) was maintained, L_(i)<d_(t), and the nozzle conformed to theother geometric parameters. Variation of throat diameter with staticL_(d)/L_(i) proportions again resulted in little or no performancedifference.

The optimum divergence angle was found to differ from those previouslydescribed in the art. It was also found that the narrowness of theoptimum range was inversely proportional to the rate of constriction.Mass throughput degraded steeply in testing outside the optimum rangedescribed. Higher rate constriction nozzles were especially sensitive.Additionally it was found that variation of intake length in excess ofthe described range substantially degraded performance especially ifcombined with a variation of the diffuser length below the describedrange.

No substantial mass flow difference was noted between truncated andnon-truncated nozzles of the same rating, indicating that the truncatednozzle might be more efficient simply based on its geometric coverage ofthe wind plane, and therefore preferred. Additionally a 2.75 nozzle hada secondary quadric layer applied after its initial phase of testing. Aperformance improvement based on power capture was noted. Additionallythe nozzles were tested in staged and nested configurations wherein inthe first case the nozzles were tested at some nominal separation withlittle or no performance degradation. In the second case nozzles werenested within each other with the smaller being placed at a nominaldistance rearward of the larger throat to achieve better throughput onhigher rate constrictions.

As detailed in the previous section nozzle flow acceleration is premisedon the principle of conservation of mass. Bernoulli and Navier-Stokesequations are considered the governing equations for fluid flow atstandard pressure and density. This regimen is generally known as thecontinuum regimen wherein a fluid model is based on macroscopicproperties. Navier-Stokes equations are usually solved numerically as nogeneral solution is known. In addition to these approaches there arevarious numerical methods applied to fluid flows ranging from LatticeBoltzmann to Monte Carlo methods. At some level however most of thesesolutions are based on empirical adjustment of the theoretical result tomatch test data. Additionally there is very little wide-scopeexperimental data regarding the performance of nozzles. Gibson and Reidprovide the most comprehensive data in the art but in both cases thestudies are limited to isolating the effects of one characteristic ofthe nozzle such as 2 dimensional divergent length in Reid. Most recentwork is premised on numerical estimations or design testing.

Numerical studies such as Tekriwal use pressure variables to calculateaccuracy of numerical simulation against empirical pressure data, butignore flow rates or derive flow rates from the pressure variables.Additionally the basic assumptions therein are based mainly on the workof Gibson and Reid which are relatively constrained in scope.Problematically prior art provides no satisfying explanation for thenozzle's improved function with the divergent section in the subsonicregimen. Likewise there is little research on the actual properties of aflow along a gradient. Formulas such as the linear interpolationpressure gradient force (PGF) equation,

${{F\left( {m/s^{2}} \right)} = {\frac{1}{p}*\frac{p_{1} - p_{2}}{n}}},$approximate flows reasonably well but do little explain the mechanismsof the flow itself or the properties said flow displays either atinitial condition or in steady state. As can also be seen thesimultaneous use of the pressure and density terms is problematic.

This can be said generally of the fluid dynamics equations. They arevery good for approximating performance under specific conditions,usually pressurized, but generally the solutions do not matchexperimental data closely in the area under consideration, e.g. mismatchbetween theoretical performance and test data that is especially true ofnozzles. The almost complete lack of research in non-pressurizedconditions adds to the imperfect understanding of nozzle function. Thedivergence between experimental data and theory is usually explained byvariation of a real gas from an ideal gas or frictional effects or someslight error in fabrication. More likely it is due to oppositionalgeometry enhancing flow effects that would otherwise by masked by thefree volume proportions of single-body research.

Since single-body constitutes the majority of solid body research dataand the basis of Prandtl boundary layer theory and Blasius' work, theerror rate in predicting nozzle performance is a strong indicator thatthere are some inherent flaws to understanding the mechanics of flows asembodied by the fluid dynamics (FD) equations. For these reasons extanttheory does not provide a solid basis from which to optimize nozzledesign in and of itself. Given the dearth of experimental data in thearea especially in the subsonic regimen this means that use of extanttheory to enhance design is mainly educated guesswork.

Since an efficient nozzle design is one of the purposes of thisinvention, it was desirable to develop a flow model which indicateddifferent design paths by which a nozzle might be optimized, one whichexplained the interaction of the various nozzle regions and whichmatched experimental data. This requires a detailing of the problemswith the current set of assumptions and development of a model of thetypes of flows a nozzle such as the designs described herein are likelyto encounter in operation and thence a more in depth description ofsolid body interaction with said flows.

The most pressing problems in this regard may include, assumption ofsolid body interaction being substantially similar regardless of thetype of fluid flow, use of the Pressure Gradient “force” (PGF) toexplain the mechanism of fluid flows, assumption that subsonic flow inthe continuum regimen is of uniform density, assumptions associated withthe distinctness of free-stream and boundary layer, assumption thatpressure can provide a substantially accurate description of fluidbehavior, assumption that pressure, velocity, and density aresubstantially differentiated variables, and the like.

First there are two distinct conditions that result in fluid flows. Oneis when a displacement volume is introduced into a fluid system thatresults in the distribution of the momentum from the volume ofintroduction throughout the system until the system again reaches astate of equilibrium. Two is when energy is introduced into a fluidsystem that effects the system-wide distribution such that flow iscreated by the properties of the imbalance in distribution and continuesuntil a state of equilibrium is again reached. Solid body interactionwith a flow that is substantially of one type or another must, by itsvery nature, have different parameters. Any given flow is likely toinclude elements of each type of flow (e.g. a plane flying into aheadwind), but the majority of interaction in a given localized systemcan usually be ascribed to one or the other. These two types of flow arebest described as wake flow and gradient flow. In the first caseintroduced force drives the flow, whereas in the second case densitydrives the flow.

This brings us to a second adjustment with regard to the current modelof flows. Both the macroscopic and microscopic properties of a fluidflow are describable by revising the variable set used. In this regardthe Bernoulli equation can be characterized as a statement of proportionand, while useful for measurement, it is not very useful for mechanics.The macroscopic pressure-velocity relationship is simply a convenientdescription of the proportion of unidirectional net momentum vs.omni-directional momentum at the molecular level as determined by thethermal/energy properties of the system in question, wherein theunidirectional component is the bulk velocity and the omni-directionalis the bulk “pressure”. In the case where this net flux across thesystem in question has not been caused by displacement, there is onlyone potential source—statistical movement based on the kinetic energy ofthe molecules in the system and a variation in molecular density.

This can be most conveniently viewed in the context of an n-dimensionalmatrix for which the population of the matrix has n degrees of freedomfrom state t to state t+1 wherein the probability of any given path issubstantially equal and random and the population is constrained toshift position at every time step, e.g. Brownian motion. The desiredsampling rate of said matrix would be the mean molecular separationalthough the matrix can be scaled to represent the mean properties ofgroups of molecules. If the matrix is subjected to a sparse-densemapping wherein the population of the matrix is denser in area a than inarea b, then the statistical net momentum/movement, e.g. flow, is foundin the dense to sparse direction. Providing an approximation of thermalenergy input into a system by constraining density variation at eachtime step to be substantially similar to the preceding time step, thismethod of representation provides a close approximation of short-termsteady state flow as one might find in a wind system.

From this model it is clear that gradient flows are a statisticalexpression of the density variation in a system and the level of kineticenergy present in the system, not the product of PG “force”. Thereby thecontinuum assumption of uniform density in a fluid flow in the subsonicregimen is clearly at odds with the mechanics of the flow itself.Therefore the assumption of uniform density must be held to localconstraints of intermolecular repulsion and thermal expansion.

Additionally it can be seen that both the macroscopic properties ofvelocity and pressure are functions of the microscopic properties ofmolecular density, root-mean-square (RMS) velocity, and translationalmomentum. In this regard these macroscopic variables can be done awaywith in favor of the more accurate model. This revised model must now bedeveloped to be of use in solid body design. The first step therein is adefinition of the mechanics of the flow.

Similar to the rest energy calculation the potential maximum of the flowin terms of energy or velocity can be calculated based on aninstantaneous unidirectional flow, e.g. all molecules flowing from astandard density region to vacuum, by setting the velocity equal to themean RMS velocity of the mass under examination. In this way anyportional flow can be characterized as a percentage of the RMSunidirectional velocity.

Since velocity can be expressed as a function of momentum and mass, thevelocity of a given intermolecular slice can be expressed as the nettransfer of momentum and mass between slices with the mass transferbetween the slices determined by the density: sparsity difference. In asteady state flow this transfer would be constant between the slicessomewhat similar to a cascade effect.

In this regard there will be a net momentum increase between any givenpair of slices, n_(n) and n_(n+1). At each slice n₁, n₂, n₃ . . . n_(n)the momentum increase will be additive in the sparse direction as eachslice has a net momentum increase between samples t and t+1. Thereby thevelocity profile of the gradient field is dependent on the specificdense sparse distribution of molecules for the field in question and thesum of momentum transfer and number of slices within the field.

In this way the macroscopic properties of velocity, e.g. the bulktransfer of mass over a given distance, can now be represented by themicroscopic fluid conditions and more specifically the microscopicmomentum field.

This is of special import with regard to the introduction of a solidbody into the gradient field. Specifically with regard to nozzles thisimplies that the velocity increase at the throat is no longer a functionof mass conservation as in the continuum model. Instead it results fromchanges in the density gradient field caused by the introduction of thesolid body and differences in the momentum transfer resulting from thosechanges.

The nature of the field in the steady state may be such that the maximalvalue the rate of momentum transfer may be concurrent with the maximalrate of change in the density gradient wherein said rate of change canbe assumed to be non-linear and likely parabolic.

With the uniform density constraint relaxed and the bulk properties nolonger dependent on mass conservation, this has substantial implicationswith regard to boundary layer. Assumptions of the distinct separationbetween conditions in the boundary layer and the freestream are nolonger valid as the foundation for the boundary and freestreamseparation is the mass continuity of the freestream.

It is useful now to treat the nozzle as a separate field within thelarger density field. Assuming steady state condition for a nozzle in agradient flow, the maximum rate of constriction for a radial inletnozzle occurs at the leading edge of the nozzle inlet. This implies thatthe greatest density change within the nozzle field will occur in theregion of the leading edge. Density will increase proportionally to thelocal rate of constriction and the thermal constraints of the field andthereby momentum will increase in the flow direction at a similar rate.

This has several implications for the visible boundary layer. While somemomentum is lost in the LE region as incident molecules collide with thenozzle wall, subsequent collisions should conform to general parametersof elastic collisions between molecules. Thereby there exists a mean(e.g. statistically directional diffuse reflection) direction of the nmolecules incident to the LE, with some parameter of momentum loss. Themomentum vector of the molecules deflecting from the LE region willreflect into the stream upon each collision while the individualmolecules will continue to collide with incoming molecules on a meanfree path basis until the initial incident path becomes closelyorthogonal to the nozzle wall. Under this model there is a formation ofa boundary layer which satisfies the no slip and visible boundary layerconditions but this boundary layer does not contain the momentum as isassumed in extant boundary layer theory.

With regard to design optimization this implies that the LE vector is ofsubstantial importance in transferring momentum into the inward intakeregions. Additionally this implies that there is a relationship betweenthe rate of constriction and parameters of the LE dependent nozzlefunction as is borne out by experimental data.

Conversely there is a limit at which the density increase becomes suchthat the net momentum transfer from the external field into the LEregion is opposed by the density increase such that there is alsoprobabilistic momentum transfer in the direction generally opposite tothe flow engendering mass loss. Such a condition leads to theentrainment of less mass into the nozzle and mass and momentum loss tothe exterior of the intake and a lesser rate of momentum transfer to theinward regions of the intake.

This condition can be experimentally observed most easily in aconverging nozzle. In a converging nozzle as the rate of constrictiongrows the rate of velocity increase is noted to shrink indicating a massbuild up in and forward of the intake. This is observable in smokevisualizations of converging nozzles wherein when the rate ofconstriction becomes sufficiently large the flow becomes stagnant to thepoint where the observable boundary layer does not form. Length overwhich the constriction occurs also contributes to this effect. It canalso been seen in the attachment of shock to a solid body in the sonicregimen.

A velocity increase is noted in the use of a converging nozzle usuallyat much lower rate than the theoretical increase. An examination of thedensity gradient in the converging section is of interest here. As theLE density condition increases a region of additional sparsity iscreated rearward of the LE. In the case of a strictly converging nozzlethe exterior field density at the throat is not a sufficient gradientfor the flow to attain a rate of momentum sufficient to clear the LEdensity and allow the full mass available at the intake to enter thenozzle.

Under such conditions it is likely for the momentum field to beparabolic achieving a maximum rate within the inlet where the rate ofconstriction acts as a counterbalance to the potential maximum rate oftransfer.

As a note this model also serves to explain the experimental differencebetween radial and straight inlets. In a radial inlet the maximum rateof constriction is localized to a relatively small region wherein thedensity increase is localized. Conversely a straight or funnel inlet hasa constant rate of constriction creating a constant density increasethrough the intake to the throat.

With a localized density region at the LE the diffuser functions toincrease the dense sparse rate of the gradient field which the nozzlecontains. The increased diffuser length with increased constrictionserves to increase the volumetric ratio by which the gradient iscontrolled and thereby clear the forward density in the LE region. Basedon the rate of constriction and thereby the rate of LE density increase,the length of the diffuser determines whether the rate of maximummomentum transfer is at or close to the throat.

If this maximal rate is clear of the intake region, a condition existssuch that the increased density is cleared and the limiting conditionresulting in flow opposing the flow field is not reached. The increasedvelocity at the throat is thereby due to the combination of the gradientbetween the LE region and the exit and the initial momentum influx fromthe exterior field. In this regard the diffuser serves to control boththe properties of the gradient field and the rate at which the mass andmomentum transfer occurs from the throat to the exit.

In embodiments, this describes the basic function of the nozzle regionsunder a revised model. This model delineates the properties of thedifferent nozzle regions and provides a foundation both for theexplanation of regional function and the design of high throughputnozzles. In illustration of the above discussion, FIG. 27 depicts anozzle with truncation intake and exit 2700, FIG. 28 depicts a Nozzlewith truncated intake and 1/r−0 interpolated curvature 2800, and FIG. 29depicts an arc section diagram for inlet geometry 2900.

In embodiments, aspects of a variable blade rotor are presented. Avariable blade number-type rotor is described wherein the number ofblades a rotor presents to the flow varies with flow speed. In anembodiment, FIG. 30 depicts a six-blade open configuration 3002, showingthe primary 3004 and secondary 3008 blade, and the primary 3010 andsecondary 3012 hub of the pressure mechanism. As is well known in disctheory, rotors with different numbers of blades and different profileshave performance profiles that closely fit a given flow velocity range.Since it is desirable to optimize the power output of a flow drivenpower device, a rotor that adapts the disc solidity presented to theflow would be more efficient at gathering power across a variety ofspeed regimens than a fixed solidity rotor.

A 3-blade rotor efficiency plot 3100 is shown in FIG. 31. C_(p)represents the proportion of power available at the area covered thatthe rotor is able to convert. This is a direct result of the rotationalspeed as it relates to tip/blade speed and the loading of the rotorthrough the generator. The power plot of this relationship forms thewell-known power curve.

FIG. 32 shows a Weilbull distribution of annual velocity 3200. Taken incombination these result in FIG. 33, a comparison 3300 of a 6>3-bladeC_(p) profile and a 3-blade C_(p) profile for annual power: velocitydistribution. As linear velocity increases, tip speed increases, and therotor reaches a limiting rotational value based on the aerodynamicproperties of the blades and disc solidity making the typical 6-bladedrotor inefficient in the ranges above 6 m/s.

While this efficiency range is highly dependent on the loading schemeboth with regard to the gearbox/transmission and electrical loads,assuming an optimized design for both mechanical and electrical loadingthere is a clear efficiency limit to a blade set based on its rotationalspeed. Enhanced loading schemes, as plotted 3400 in FIG. 34, that shiftthe rotational aerodynamic efficiency range upward without negativelyeffecting efficiency of power capture are preferred in this invention.That said, in the 1 m/s to 6 m/s range the 6-bladed rotor captures moreof the KE available in the raw flow. Given a situation wherein themajority of a given flow on a time period basis is in the lower rangesthe advantage of having variable disc solidity is clear.

The variable solidity rotor may have a plurality of prime number rotorssets (e.g. 1, 2, 3, 5, etc) co-axially mounted inclusive of a facilitywhich allows the secondary, tertiary, . . . nth rotor set to slot intoeach preceding set. As an example, for a 3 blade primary rotor withthree sets, the initial stage would be a 12 blade rotor which wouldclose to a 6 blade rotor and then into the primary set of 3.

The facility for closing said primary rotor sets may be inclusive ofboth dynamic pressure driven and/or actuator/mechanical methods. Rotorsets can either be of closely similar properties in terms ofaerodynamics and mass or of divergent blade structural, mass, andaerodynamic properties.

In embodiments, rotor sets may be mounted to a series of dual positionslip rings wherein when the dynamic force on a given set is exceeded thering is released and dynamic force on the blades shifts it to a closedposition on the following set of blades. A mechanism is slotted onclosure such that when the dynamic force on the closed blade setsindicates a drop in velocity the blade set is released to open position.

In this embodiment the rotor is constituted of 3 sets wherein theprimary set is a structurally reinforced swept-twist thin airfoil bladeand the secondary set and tertiary sets are thin swept-twist airfoils.The camber geometry of the secondary set is fitted to the lower surfaceof the tertiary set and similar fitting geometry is used for the primaryand secondary sets. Geometry is such that the blade pitch between statesis not altered. Each set is optimized for higher-speed profiles, toextend the usable range of each blade state to maximum efficiency.

In embodiments, the primary blade set is inclusive of structuralcomponents that allow mass distribution to be controlled on the rotorper provisional application. FIGS. 35-38 show certain aspects of theblade configurations previously discussed, where FIG. 35 depicts openposition 12 blades 3500, where velocity is approximately in the range of1-3 m/s, FIG. 36 depicts open position 6 blades 3600, where velocity isapproximately in the range of 3-6 m/s, FIG. 37 depicts closed position 3blades 3700, where velocity is approximately 6+m/s, and FIG. 38 depictsa sample of open and closed profiles 3210, where the open profile showsthe primary blade 3802, the secondary blade 3204, and the tertiary blade3208.

In embodiments, an inertial rotor may provide advantages by enhancingrotational stability under dynamically variable conditions, wherein theoutward centripetal force of the rotation is used to enhance the inertiaof a rotating body by way of a variable radius mass distribution system.A material may be allowed to move based on centripetal motion toward theouter radius of the rotating body. This can be executed with anymaterial that can be controlled in its balance under centripetal force.Said material can also be controlled by way of actuators.

In embodiments, an inertial rotor may be comprised of single orplurality of rigid or semi-rigid bodies symmetrically or asymmetricallyjoined in a contiguous or non-contiguous manner around a centroid ofrotation wherein there exist facilities to control the mass distributionwithin the plane/planes of rotation and thereby the inertialcharacteristics of said rotation in a manner advantageous to the desireduse.

In embodiments, the invention may constitute a rotatable body 302, asshown in FIG. 39, with a central mass reservoir 3904, a facility forcontrolling said mass 3908, and an outer mass reservoir 3904. Saidreservoir can be either a single or plurality thereof. The initialcondition is with the mass central to the axis of rotation wherein thereis little additional energy required to begin rotation. As the body'srotation accelerates the mass may be moved toward the outer radius 3910and 3912 through the mass control mechanism 3908, which may include butnot limited to centripetal acceleration or mechanical or otheractuators. The additional mass in rotation on the outer portion of thebody provides a more stable rotation with greater relative inertia.

In embodiments, the control of the mass within the rotor radius may beachieved by way of variable mass flexible structures, e.g.weights/springs or memory plastic/foam or other suitable material knownin the art, wherein the flexible structure, with an external element ofthe structure having greater mass than the internal element, iscontained in an housed chamber extending axially through a single orplurality of solid bodies. As rotation and centripetal force increasethe weight will extend the flexible structure to the maximal desiredexternal radius of the rotating body. As detailed below these structurescan include magnetic properties of use in both mass distribution controland field generation.

In embodiments, a contiguous substance is housed within a single orplurality of central portion/s of the rotor assembly wherein channelsextend axially through a single or plurality of bodies attached to saidcentral hub. The substance can be any substance that conforms to a givenviscosity wherein the substance will shift mass toward the outwardradius through the channels only under rotation while maintainingcontiguity through the radial channels and central hub such that ascentripetal force is reduced the viscosity (coherence) of the substancewill draw the outer mass back into the central hub. As detailed belowsaid material can also include magnetic properties of use in both massdistribution control and field generation.

In embodiments, a fluid may be allowed to cycle through a single orplurality of axial channels. Said fluid can be a standard dense fluid orcan be fluids with special properties such as magneto-rheological fluidswherein the electro-magnetic properties of the fluids can be used tocontrol mass distribution within the solid body under rotation. In sucha rotating body the magnetic fluid, or other magnetically “enhanced”substances or structures such as those mentioned above, while beingcontrollable in its distribution through the body by way ofelectromagnetic fields may also serve the purpose of generating usefulelectro-magnetic fields as the substance or structure achieves itsmaximal radial position. Such executions of the current invention can beachieved with either a fixed method of field generation or incombination with a single or plurality or counter-rotating bodies. Inaddition, mechanical actuators may be used to granularly control themass distribution of the substance or structure under consideration.

FIGS. 28-31 show embodiments relating to aspects of an inertial rotor asdescribed herein, where FIG. 40 depicts a weighted structure initialposition 4000, FIG. 41 depicts a weighted structure in a subsequentposition 4100, FIG. 42 depicts a 3 blade structure in motion 4200, andFIG. 43 depicts a 3 blade structure 4300 with mass control channel 4302and central mass reservoir 4304.

It may be advantageous to reduce the cost and weight of the structuralsupport of an accelerating array. It may also be advantageous to reducethe assembly cost therein either through methods or specific mechanisms.It may also be advantageous to reduce lifetime component replacementcosts through use of modular components. It may also be advantageous tohave supporting structures that are only partially integrated with thearray, serving only a structural support function for one or morenozzles. A number of methods for doing this are described including“fractal” space frames, methods of installation and maintenance, methodsof supporting or suspending arrays, and the like.

In embodiments, the present invention may provide for structuresutilizing fractal configurations. Referring to FIG. 44, a fractal spaceframe is depicted wherein the geometric structure of the space frame isrepeated in the members of the space frame to the nth iteration. Inembodiments, the smallest scale iteration or the nth iteration may betermed the base member, and the polyhedron that forms the basis of thenth iteration member may be termed the basis polyhedron. FIG. 44 showsan image of the top and side elevations of a basis octahedron.

A fractal space frame is a 3-dimensional fractal. A fractal space framemay use a regular, Reuleaux, Kepler-Poinsot, and like polyhedralstructure, or a form incorporating multiple polygon types such as azonohedron or a combination thereof and may be made of composites,metals, or other like materials that can be molded or fabricated.Fractal space frames may include classes of structural members that arein tension or compression or a combination thereof. They may includeboth uniform or regular structures, such as in a geodesic space framethe basis members could formed from triangular or some other polygonalvariation of a truss, and non-uniform or irregular structures such astensegrity structures. Structural variations that can be used for thebasis member include but are not limited to structures such as bundledcolumn structures, tensegrity structures, diagrid structures, allclasses of truss structure, and the like.

Referring to FIG. 45, to form and stabilize a member structure somevertices may be shared and additional members may be added to connectsome vertices (side elevation image below). Generally the polyhedraltype may match the characteristics of the element being supported by thespace frame.

Members added to the polyhedra to construct the elongated member formmay be added at the vertices forming the maximal circumference underrotation or at vertices within the maximal circumference, such asdepending on the desired load bearing properties, orientation of thepolyhedra under consideration, and the like.

“Fractal” space frames may be fabricated by a number of methodsincluding molding, lay-up, filament winding, welding, assembly, and thelike. In the case of a filament wound space frame polyhedra skeletonsmay be found in a base member. A different or the same method ofmanufacture or assembly may be used for the various iterativecombinations of the space frame.

Referring to FIG. 46, the image shows a side elevation of a threeiteration octahedral space frame wherein the space frame members mayinclude the edges of a polyhedral series, where the space frameconnectors are found at the vertices. Additional members in this casemay be added at the maximal circumference.

The advantages of a “fractal” space frame may include low solidityrelative to structural and loading capacity thereby reducing the costand weight of the structure under consideration.

In embodiments, the global structure of the space frame may additionallybe fractral based on local conditions. In this case the initial fractaliterations may be in the vertical or horizontal dimensions and adaptiveto the local load bearing requirements based on the number of verticalor horizontal layers. and further iterations define the membercomponents of the edges of the series polyhedral skeleton at the desiredlevel of iteration.

It may be of benefit to have a method by which an array may be modularlyconstructed and maintained. A structure is described herein that mayinclude an installation facility for both the supporting and producingcomponents of an array where the facility may include a platform, amethod of elevation, a method of placing components of the array, amethod of removing components of the array, and the like.

Referring to FIG. 47, the image shows an embodiment of an acceleratingarray, wherein the array is constructed and various components areinstalled by way of at least one installation platform, at least oneinstallation crane, at least one exterior or interior method ofelevating the same, and the like, including a spaceframe 4702, elevationtowers 4704, a crane 4708, an installation platform 4710, a bearing andplatform 4712, and a foundation 4714. FIG. 48 shows embodiments of adrive sheave structural member, in a front elevation FIG. 48A and sideelevation FIG. 48B.

The bearing may additionally be modular. The bearing may have n modularelements that form the bearing as a whole wherein each element has anexternal or internal sliding element and may be removed and replaced inthe case of failure or maintenance independently of the other elements.In case where the bearing is a sealed bearing the modularity may requirean alignment and locking facility to replace the modular element. In thecase where the bearing is not sealed a mechanism by which the localizedload may be relieved from the modular element to facilitate removal maybe necessary. The number of modules in the bearing may be determined bya solution that minimizes installation and assembly complexity and costwhile allowing the removal a single module and the temporaryredistribution of load on the remaining modules during the replacementoperation.

Various methods of operation of achieving same are disclosed wherein theinstallation facility and associated facilities may utilize an elevationmechanism with more than one drive element integrated into the spaceframe, an elevation mechanism with more than one drive mechanismintegrated into columns at the corners of the array, an elevationmechanism that has multiple drive elements integrated across the array,and the like.

Alternative methods of constructing an array of nozzles modularly ornon-modularly are described. It may be advantageous to minimize the massand materials use or weight of both the space frame and the nozzlecomponents in an accelerating array. Methods of creating arrays andinstalling nozzles within single space frame, suspension, buoyant, andthe like, or combinative structures are examined.

Referring to FIG. 49, one embodiment may be a single “mast” frame with amain space frame 4902, suspension wires or cables 4904, structural boom4908, and the like, where a flexible nozzle material such as latex,coated fabric, and other like flexible materials. A non-flexiblematerial, such as a thin wall molded co-polymer, may be secured to thethroat and the polygonal vertices of the exit and/or entrance and/or aframe that may define the truncating polygon at least one of the exitand entrance. In embodiments, these may be installed in situ ormanufactured separately for modular installation. The mast frame may beconstructed from readily available members such as HSS or I-beam or thelike as any class of framed construction such as staggered frame,bundled columns, diagrid, and the like, or may be a constructed offractal elements mentioned above. The structure may be singular anduniform in depth and width or may be non-uniform such as I or H crosssection or a more complex polygonal cross section that would include thevarious classes of beam cross sections that may be designed to maximizehorizontal and vertical load resistance and minimize material use. Amast and boom structure may further utilize combinative tensionstructures for both the lateral and the mast support. The tensionstructures may be simple as in a tension frame or may have complexrigging in either the vertical or horizontal dimensions.

An example of such complex rigging might be where tension wires aresupported by two perimeter columns and rigged in a diagrid pattern andthen locked together at the nodes. The nodes may form the attachmentpoint for the mast rigging which may attach locally on or near the samerow as the nozzle mast insertion or non-locally at some optimal supportangle to a node vertically or horizontally further from the nozzle mastbeing placed. Such complex tension rigging may allow structuraloptimization for the load bearing structure such that the horizontal andvertical forces effecting the structure are more distributed or are“focused” on or “deflected” to specific areas of the structure that aredesigned to absorb the combined load density.

It may also be desirable to decompose the structure of an integratedarray and superstructure to a non- or partially integrated array andsuperstructure wherein the superstructure may be exterior to the arrayand fixed on the exterior perimeter and the array may be supported byrotating internal structures that attach to the exterior structurethrough a bearing or bearing-like facility. FIG. 50 shows an embodimentof an array 5004 and a portion of exterior structure 5002. It may beadvantageous to further decompose the structure to fixed interior andexterior columnar elements upon which a single nozzle or a row array ora row-column array of nozzles are similarly fixed on either or both theexterior column or the interior column by means of a bearing or bearinglike facility. These bearing facilities in either may include a yawsystem to assist the co-mounted array section to orient to the localflow direction.

Exterior superstructures may endow a number of advantages in terms ofreduced torque experienced by the superstructure from variation ininflow vectors in the vertical plane, increased safety, less loading onindividual bearing mechanisms, enhanced opportunity for load isolation,and the like. Exterior superstructures may also maximize the local andglobal load bearing properties of the superstructure for both horizontaland vertical loads by creating greater beam depth with respect to windloading and greater diameter with regard to bearing loading.

As illustrated in FIG. 51A-E, an exterior superstructure may be circularas in a space frame “tube” inclusive of rectangular, polygonal, orcircular cross sections or may be more complex in its perimeter crosssection. The exterior superstructure may involve a single layer on thestructural perimeter or multiple layers on the outer or inner perimeter.The cross section may be n-pointed star polygon or any an n-sidedregular or irregular polygonal structure of variable or uniformcomplexity that provides local and global load bearing advantages to thestructure. The structure itself may be a single or multiple regular orirregular polyhedra wherein the constraint is that the interior of thepolyhedra be uniform or roughly cylindrical. This would include allclasses of regular, irregular, anti-prismatic, or prismatic polyhedraand the like with the types of cross sections mentioned above. FIG. 52and FIG. 53 illustrate embodiments showing basis polygon members 5202configured with polyhedral members 5206 mounted with the bearing 5204.The basis members of the frame connecting the vertices of the polyhedramay be placed to maximize the load bearing capabilities and minimizeweight and density of the superstructure. The members may be acombination of compressive members or tension members. This may includegeodesic variations, tensegrity variations, and the like. In addition tobeing optimized for load bearing the superstructure may also beconstructed in such a way as to provide minimal flow resistance to theinterior of the structure. This may include shaping or cladding themembers or designing the structure such that the width and profile ofthe members is minimized. Such parameterization provides advantages bothin terms of the yield of the interior array and in terms of reducing thewind load on the structure overall.

As in other iterations of the invention with regard to thesuperstructure and modular assembly of the array, in the case of theexterior structure, the properties of the structure may be designed insuch a way as to allow easy extraction of a single module or multiplemodules from an array within structure. As in other iterations this maybe performed by an installation and maintenance facility constituted ofan insertion and removal mechanism, an elevation mechanism, and thelike.

An exterior superstructure may additionally be uniform or non-uniform inits geometric properties with regard to its dimensions in the verticalplane. Additionally the local polyhedra may be optimized for thespecific load bearing properties of given level. For example, a10-pointed polyhedra may be optimal at ½ the height of the structurewhereas a 12-pointed polyhedra might be optimal at ¼ the height of thestructure. Members may be limited to spanning a single polyhedralsection or span multiple levels of the polyhedral sections.

An array of modules within an exterior superstructure may be mounted onthe superstructure either as single or multiple row arrays. The rowarray/s may be attached to the superstructure by means of a bearing, aroller, or rail system, or by other means of mechanical or fluid inducedrotation. The row array/s may be attached to the interior structure orthe exterior or both by means of a mechanism of rotation. The mechanismof rotation may be roller drive and yaw system, a rail drive and yawsystem, a slewing bearing and yaw system, a roller bearing and yawsystem, a magnetic bearing and yaw system, a Teflon slide bearing andyaw system, and the like or a combination thereof. The row array/s maybe attached to the rotation mechanism by means of single or multipletrusses or space frames in depth wise or horizontal or angular directionor a combination thereof, of tension wires in the depth-wise orhorizontal or angular direction or a combination thereof, and the likeor a combination of tension and compression members. The row array/s maybe mounted within the support members, on the support members, below thesupport members, or above the support members. These members may attachto rotation mechanism within the same plane as the row array/s orexterior to the plane of the row array/s either in the upward ordownward direction to provide additional load bearing capability.

The exterior superstructure may be constructed and manufactured orfabricated by means of and of the classes of materials described inprevious iterations of the invention. In addition to the space framemembers including members in both tension and compression the perimeterframe may include elements of tension and compression. This may includeguy wires attaching the columnar structure of the perimeter to acounterbalance mechanism such as a piling foundation.

In embodiments, the present invention may provide for buoyantfacilities, where the module may include a nozzle that may be formed ofa flexible or rigid material, where the structural rigidity may beprovided by method of internal pressure and a minimal shape skeleton orby the material itself or a combination thereof, and where the method ofproviding internal pressure to “inflate” the nozzle may be performed bythermal energy or pumping, such that the nozzle is comprised of a singleor multiple bodies that contain a volume or volumes of fluid that can beused to achieve a buoyant condition. Buoyant nozzles may include allclasses of nozzles described in this and previous iterations in theinvention wherein the interior surface of the nozzles is one of thebuoyant surfaces and the bounding polygon or circle or the like fromwhich the nozzle geometry derives forms the other surface and the volumecontained therein provides the buoyancy. The bounding geometry may beextended to curvatures greater than 0 to provide higher buoyancy forsmaller nozzles wherein sufficient volume is not enclosed within theoriginal geometry described above.

The method of inflation or pumping may be such that it provides buoyancyto the nozzle such that all or a portion of the dead load of the moduleis neutralized by the degree buoyancy. The medium of buoyancy may be airor other fluids that provide the buoyancy by decreasing the density ofthe fluid within the enclosed geometry through thermal input or it maybe a fluid that has a naturally lower density such as hydrogen or heliumor a combination of both methods. The nozzle may be formed of anymaterial which will maintain the density balance between the interiorand exterior fluids such as all classes of treated woven materials, allclasses of flexible rubbers and polyurethanes and the like, all classesof rigid materials such as polymers or copolymers or syntactic foams orplastic foams, and the like. The nozzle body may include a single ormultiple uni- or bi-directional valve mechanisms by which the density ofthe interior of the nozzle may be maintained at a given level andthermal control mechanism to achieve such an end. The nozzle body mayinclude various methods of thermal input such as resistive componentsand the like that produce heat through as electrical charge or chemicalreaction or may include gas contained in pressure vessels wherein alighter than air gas is used to achieve buoyancy and the gas is releasedwhen the enclosed volume density exceeds a given level.

It may be advantageous in the case of a buoyant module to reduce theweight of any given component especially generators. The power producingcomponents of the module may utilize generators which minimize weight topower ratios such as superconducting generators and the like. Similarlythe structural elements of the nozzle such as the membrane andstructural members that maintain the shape and support the internalcomponents may be made of lightweight materials such as carbon fiber oraramid fibers and the like. The structural material may further be anyof a class of rigid or flexible impregnated foams wherein the foam isimpregnated with a gas that provides direct buoyancy to the structuralelements of the module. These could include structural elements made ofsyntactic foams wherein the microspheres or any interior space/s areimpregnated with hydrogen or helium or may include classes of foamingagents and polymers or copolymers wherein the foam is impregnateddirectly in the foaming process or after the foaming process is completewith a lighter than air gas.

Buoyant modules may be attached to a tether and thereby to an anchoringmechanism either singly or in arrays or may be attached to asuperstructure. Arrays of buoyant nozzles may be attached to each otherand a tethering mechanism by means of metallic or composite cables or acombination thereof and the like wherein the strength to cost ratio isoptimized. Metallic or composite tethers may similarly be used to attachan array of buoyant modules to a superstructure such as those describedabove or in other iterations of the invention. The cable mayadditionally include an embedded or separate means of power transfer. Abuoyant array may also include the means to adjust the elevation ororientation of the array to seek optimal power producing conditions.

Referring to FIG. 54, another embodiment may be a nozzle wherein theshape of the nozzle provides a release area or channel for over-densityconditions that may be found in the nozzle. The release may take theform of a single or multiple vortex or swirl mechanism/s, bulbousfeature/s, drill through mechanism/s, and the like or a combinationthereof. Bulbous features may include macro and micro uniform ornon-uniform features such as an annular inverted semi-ring or ringsaround the rotor wherein the depth of the ring/s is formed smoothly oracutely from areas forward and rearward of the throat, or a weightedannular semi-ring wherein the area of maximum depth is forward orrearward of the central diameter of the ring/s, or a continuous ornon-continuous annular semi-ring/s, or the like. FIG. 55 shows examplesof nozzle cross section profiles 5501-5505. Drill through features mayinclude uniform or non-uniform drill through in the flow-wise direction,in an angular or spiral configuration, densely or sparsely packed drillthrough mechanisms, uniform or non-uniform placement in the directionorthogonal to the flow, mechanisms placed in the forward and/or rearwardsections of the nozzle, circular arrangements or polygonal arrangementsor random arrangements, and the like or a combination thereof FIG. 56shows examples of drill through patterns 5601-5606. In the case ofnon-uniform drill through the rearward portion of the drill through maybe expanded as in a diffuser to assist clearance of over-densityconditions at or around the inlet of the drill through. This may beutilized in both the intake and exit regions of the nozzle in the casewhere an annular “relief” ring is present or may be utilized from theintake to the exit in the case where an annular ring is not present or acombination thereof dependent on the local topographical features as ina non-contiguous annular feature. As in previous embodiments thesefeatures may be applied to uniform or non-uniform scalloped nozzle walltopography. Another embodiment may be the use of uniformly ornon-uniformly 3-dimensionally tessellated surfaces in flexible ornon-flexible materials to enhance flow or structural properties of thenozzles.

It may also be desirable that the least expensive materials and/ormethods of fabrication or manufacture be considered in production ofoptimized space frames or nozzles.

Another embodiment may be where the nozzles mentioned above are mountedinto contiguous n×m arrays, where n is greater than 2, within asuperstructure or a buoyant array as in previous iterations of theinvention. Additionally this may include other types of nozzles oraccelerators such as wide-angle uniform and non-uniform nozzles. Thismay include the classes of nozzles known as diffuser augmented turbinesor super-venturis or nested nozzles and the like. These nozzle types maybe fit into a superstructure in substantially the same way as previouslydescribed, e.g. mounted at the perimeter or onto a central supportmember or onto a tension member such as a wire or a combination thereofand the like. Additionally in the case of the diffuser augmented turbineor other types of non-uniform nozzles this may require additionalcomponents or shapes forward of or around the inlet to reduce the effectwind pressure on the diffuser and thereby the array. It may be desirableto have such mechanism to reduce wind pressure coefficients or theexpense of the superstructure or anchoring mechanism in the case buoyantiteration may be such that the technology becomes non-viable.

Another embodiment may be an array where a square truncation of thenozzles described above or nozzles described in previous iterations maybe rotated 45 degrees to form a diamond array or diagrid wherein theangles forming the diamond may be uniform or non-uniform. The diamondarray may have the advantage of tangential structural support similar toa geodesic space frame while allowing a square truncation and increasednozzle packing

In embodiments, rotor profiles may be optimized for accelerating nozzlethroat conditions. It may be desirable in accelerating arrays to utilizerotors that are optimized for high-speed rotation or high-torqueconversion. Wind turbine rotors may operate in instantaneous dual flowconditions. One flow may be the inflow that drives the rotor and theother may be the crossflow over the blade as it describes its period ofrotation.

Rotors used in wind turbines may be based on airfoil profiles used forsubsonic aircraft. An aircraft profile may operate in an environmentwhere the wing may encounter flow from many vectors and theinstantaneous operating environment is a uni-flow type. This may beuseful for normal HAWT type machines as the instantaneous inflow mightbe from a variety of vectors due to turbulence or as the inflowconstantly shifts direction and the machine orients to it.

Conversely a rotor in the throat of an accelerating nozzle may operatein dual flow condition but the inflow vectors may be stabilized along asingle path. With regard to rotor profiles this may mean a differenttype of profile may be possible that would reduce aerodynamic losses andincrease the velocities at which the rotor can effectively operate andproduce power. This would be especially true as the circumferentialvelocity of the blade tips approach or enter the low sonic regimen.

Profiles that reduce interaction of the cross-flow with the inflow onthe upper side of the blade may be necessary to allow high speedoperation with minimized flow disturbance. Most research is limited towind tunnel flow over an aerofoil designed to optimize flow propertiesat various angles of attack. Given a typical aerofoil profile pitched tomaximize imparted momentum from the inflow and at an angle of attackrelative to the axially encountered fluid the boundary layer on theupper surface of the profile may be usually thickened or detached. Thismay create substantial interference between the inflow and thecross-flow such that some momentum may be deflected from interactionwith the blade or in cases of higher RPM reflected back against aportion of the inflow, thereby reducing its efficiency in convertinginflow momentum to axial velocity for a particular blade and disturbingoverall properties of the inflow with regard to the rotor as a whole.

Given the single inflow vector found at the throat of a nozzle, theprofiles used in this environment may no longer need to be optimized forvarious angles of attack as are the existing classes of profiles. Theparameter by which they may be optimized in this environment may be toreduce the mass flow disturbance over the upper portion of the blade,better attach the upper and lower boundary layers, create vortex cyclingon the lower portion of the blade to counteract drag, minimize the lowerportion of the blade's interaction with the flow or manipulate suchinteraction, and the like, or a combination thereof. It may therefore bebeneficial to design profiles that manipulate the local flow propertiessuch that inflow interaction with the blade is maximized and the axialinteraction of the inflow and the crossflow is minimized so that theeffect of each blade's passage on the rotor as a whole may also beminimized. This may lead to rotor profiles that are very different fromextant airfoils as the flow conditions they are operating in both interms of a single inflow vector and the in and crossflow environment arevery different.

Blades optimized for this environment may include either or both upperand lower surface vortex or density manipulation mechanisms at either orboth macro and micro scale. The blades may be a body or sheet profileand may include variable quadric surface geometry to reduce disturbancein the flow. These mechanisms may be variably adapted along the body ofthe blade to optimize local performance at a specific axial velocity orflow condition.

For example, a “wide” vortex generation mechanism may be used to reduceflow opposition on the underside of the blade toward the root of theblade where in a twisted embodiment the angle of the blade may be themost acute and the axial velocity of the blade may be lower or near tothe inflow velocity causing minimal axial disturbance or flow separationon the upper portion of the blade to act against the inflow such thatthe inflow itself may serve as a boundary control mechanism. Movingalong the blade where the axial velocity is increasing the blade anglemay vary to present a less acute angle to the flow, approaching apresented angle of 0 near the tip where the axial velocity is at itsgreatest value. As the angle presented to the axial fluid decreases inmay be beneficial to shift from a single “wide” vortex generationmechanism to a double “narrow” vortex generation mechanism as the axialvelocity increases. These micro and macro scale vortex generationmechanisms may be used in combination wherein the intervening profilegeometry is interpolated for two or a plurality of bounding conditions.The bounding conditions may represent the physical extremum of the bladeor arbitrarily bounded sections of the blade. These mechanisms may beindependently or combinatively utilized wherein a “large” scale vortexgeneration feature used to create globally desirable density conditionsmay include a “small” scale generation mechanism to control the localflow properties associated with the larger mechanism. FIG. 57 showsexamples of such blade shapes 5701-5708. FIG. 58 shows examples of bladeshapes, including twisted with a winglet 5801, twisted without a winglet5802, with a twisted narrow surface 5803, with a twisted wide surfaceround tip 5804, with a twisted wide surface angled tip 5805, and twistedand swept 5806. FIG. 59 shows additional blade profiles 5901-5917,including a single large vortex 5904, double medium vortex 5905, singlemedium vortex generator 5906, interactive vortex mechanism 5913, doublesmall vortex generator 5914, single large vortex, double medium vortex,and double small vortex generator 5917.

An optimal “wide” vortex generation mechanism might be designed suchthat it effects the global flow over the blade and may create areas oflow density characterized by vortex or swirl properties. The vortex orswirl created rearward of the mechanism may additionally impart someadded degree of momentum to the blade in the axial direction as it wouldbe optimal for the rotation of the vorticity or swirl to be tripped inthe direction of the axial motion of the blade. A “wide” mechanism mighthave a variable interior surface either applied globally or locally toaccess and/or enhance this effect. A blade might have iterative “wide”vortex mechanisms along a single or plurality of surfaces. The “wide”mechanism or mechanisms may be further enhanced by the placement ofvortex mechanisms along the relevant surface to enhance the massthroughput to the central volume affected by the mechanism.

Facilities to the reduce interaction on the upper surface of the bladeand drag on the lower surface may include vortex generators, uniform ornon-uniform three dimensional surface tessellation, uniform ornon-uniform flow-wise vortex edges or edge tessellations, and the like,or a combination thereof.

Specific pitch angles along the blade, degree of sweep and twist, tipvortex control, and the like, or combinations thereof may also beutilized in combination with the aforementioned facilities to optimizerotor operation.

It may also be desirable that inexpensive materials and/or methods offabrication or manufacture may be considered in production of optimizedsurfaces and profiles, as described herein.

In embodiments, the present invention may provide for rotor/loadoptimization. Methods for dual speed control of rotor and generator mayreduce rotor angular velocity and thereby reduce aerodynamic losses influid energy conversion.

In normal HAWT type wind machines it may be desirable to increase therpm of the generator relative to the rpm of the blade to maximize powerproduction. This is usually achieved through use of a transmission.

In accelerating arrays it may sometime be desirable to reduce theangular velocity of the rotor due to the increased velocity and therebyrotor angular velocity at the throat. It has been found thatcircumferential velocity of rotors in accelerating nozzles may approachlower sonic conditions at the higher inflow velocity ranges inconditions where the applied resistive load is optimized for powerproduction. This may present a limiting factor to the function of anaccelerating array.

By utilizing electrical and mechanical loading in the form of powerelectronics and/or a transmission facility, the rotor angular velocitymay be stabilized in an optimal range for both reduction of aerodynamiclosses in extraction of energy from the flow and optimization generatorrotor speed for power conversion.

In an embodiment a continuously variable transmission may be used toincrease the mechanical load on the rotor in order to slow the rotor'sangular velocity to a range where the circumferential speed is reducedbelow the low sonic regimen. At lower regimens the applied mechanicalload might be reduced or reduced to zero to maintain an optimal rotorand generator rpm.

In another embodiment the applied load may be electrical.

In another embodiment the applied load may be an optimized combinationor electrical and mechanical loading.

Additionally it may be desirable to optimize the power transfer and/orpower control networks by use of algorithms that minimize connections orresistance through connection types within the network topography ormaximize local intra-machine conditions for power production. Thesealgorithms may include combinatorial techniques, dynamic programmingtechniques, evolutionary approaches, and the like.

In embodiments, the present invention may provide for optimization ofcost/yield, where methods for global and specific optimization of costyield parameters may produce lowest COE within technological parameters.

The method of optimizing the cost to yield relationship at the globallevel may involve assigning variables to each component in anaccelerating array based on the cost of a component and itssub-components and/or basis materials, yield or loss contribution of acomponent, structural parameter of a component as it relates to loadbearing, structural parameter of a component as it relates tocontributory mass of a component to local and global load parameters,cost of manufacture a component inclusive of sub-components, cost ofassembly of a component, cost of installation of a component, cost ofmaintenance of a component, contribution of a component to maintenanceon other components and the lifetime cost of a machine, and the like.This analysis may also be applied to each component and itsub-components and basis materials and manufacturing methods if aninitial level of specific optimization was desired.

These analysis also may include the efficiency to cost parameters of theunderlying technologies such as the accelerating nozzle geometry.

Each set of component variables may then be run through its set ofpotential parameters based on the technologies or methods that can beapplied in the given component area. In embodiments, the solution setthat provides the minimal COE value for the formula,COE=Annual All in Cost/Annual Yield,may be considered to be the optimal solution given the currentlyapplicable set of input variables.

For example, the lowest cost material for the supporting space frame ofan accelerating array may be fiber reinforce plastic (FRP) but given thesize of the structural members necessary for local load bearingproperties the amount of material used might contribute significantly tothe loading parameters at each subsequent vertical level of the arraynecessitating the use of larger structural members capable of bearing ahigher load. This in turn may necessitate the use of more materialthereby increasing the dead and live loads of the machine both locallyand globally and increasing the cost of bearings, installation,maintenance, levelized cost of replacement, and the like, due toincreased stress based on the increase loading parameters.

While FRP might be the most cost effective on a per unit basis it may bemore cost effective to use a more expensive material that engenders alesser increase in the global and local structural properties of thearray, such as a carbon fiber composite. Conversely if it was found thatthe cost of manufacture for an FRP component may be significantly lowerthan the cost of manufacture for a carbon composite member, it may bethe case that FRP may be indeed lower cost on both a per unit andoverall basis and FRP would be indicated to be optimal. If however suchwere the case for initial cost, but it was found then that the increasedload resulted in the need to replace the bearing and yaw motors on anaccelerated basis it might be found that while initially more costeffective FRP might make a significant contribution to the lifetime costof the machine and would again be considered non-optimal.

As another example, yield ratings of wind machines may be set at someupper limit of extraction which in turn may define the rating of thegenerator used to convert the kinetic energy to electrical power. Thisrating may be based on a maximum inflow speed usually between 12 and 13m/s. Generally speaking the distribution of velocities in this range maybe low, such as below 5%. In this case if only 5% of annual power outputderived in the range between the maximum rating and 90% of the maximalrating, and the additional 10% of power rating contributes a cost ofweight and rating that exceeds the 5% of annual power derived in therange then using a generator with a lower rating and sacrificing theextra power may be considered optimal. This could also includedeliberately rating the generator at the lower level and allowingoperation for a certain percentage of the time at the higher rating ifit was found that such operation did not contribute significantly tohigher lifetime replacement costs relative to the higher yield achievedby such operation.

Additional factors in calculating an optimal cost/yield combination fora modular system may include calculation of likely improvement rate ofthe technology under consideration. Also considered may be the longerterm effect of material and component supply availability and itsprojected effect on cost.

It may be desirable to optimize an energy producing machine as describedin the invention based on a simultaneous optimization of yield and cost.Since the interdependencies may be complex between components having ayield and cost parameter and those that are strictly cost driven, asimple independently analyzed lowest cost and highest yield solution maynot produce an optimal balance between cost and yield with regard to thefinal cost per unit power produced. Additionally for certainapplications yield or energy density may be determined to be of greaterimportance and therefore the method of optimization may includeadditional complexities beyond the interdependencies of cost and yield.

The purpose of the optimization may be to better inform the design of agiven machine for a particular location or application or the design ofmachine classes across application or location parameterized sets. Dueto level of interdependency a recursive or partially-recursiveoptimization may produce the best results. Other methods may be used toachieve the optimal result inclusive of deterministic andnon-deterministic, genetic, decomposition, approximation,gradient-based, evolutionary, matrix, fuzzy, stochastic, empirical,statistical methods, and the like or a combination thereof.

In the method described below a recursive tiered matrix representationis used but the parameters of optimization may be applied with thebroader range of methods.

In the case, the permutations of possible design solutions may beapplied wherein the permutations are identified in an n dimensionaloptimization matrix wherein the dimensional number of the matrix may bedetermined by the number of optimization parameters under consideration.The desired result may be that each matrix value may represent aweighted cost per unit of power produced for a given designimplementation that captures all cost, yield, and other parameterseffecting the system.

For example, the ith and jth design of an optimization matrix maycapture all the cost parameters of the particular implementation, theyield of the particular implementation, and weighting ratios pertainingto the value of either parameter based on its importance for a givenmachine application. This may be because there may be applicationswherein energy density or some other parameter is considered to bewholly or partially more important than the cost of energy from thesystem. This structure may best accommodate variations withinapplications.

It may be desirable to have n optimization sub-matrices wherein eachmatrix may be assigned a tier level based on its dependencies thatcontribute to the ith, jth cell of the primary optimization matrixwherein a given matrix value may be assigned from an nth optimizationmatrix that analyses a contained subset of optimization parameters.Sub-matrices may be internally supplied with variables or may beinternally and externally supplied with variables from other matrices.An example may be the input result of a module power optimization matrixwhich may in cases be internally supplied with power producing componentvariables but externally supplied with global height, width, and depthcharacteristics that may substantially contribute to the decisionstructure of optimization. Such a matrix may also contribute to otherprimary matrix variables such as cost or weight or LRC. The basis forthe optimization matrices may be component cost or global cost modelsthat allow the modeling of various parameters affecting the cost of agiven design. Such matrices may include the basis and derivative costsas well as any formulas and equations that are contributory tocalculating the basis and derivative costs. The optimal solutions may befound by convergence of sub-matrices in the case where matrices areconstructed for all affecting variables or by maxima-minima analysis ofthe global n-dimensional matrix. Such a matrix or a base case may alsobe used initially to identify desirable design parameters or conditionsby which better design optimization may be achieved. This process may berecursive. Granular recursion may also be used wherein a boundarycondition may be used to identify regions of the optimization matrixthat fit a defined range of conditions and wherein a higher resolutionof the contributory variables may be used than the original resolutionof the matrix and may be useful to identify the precise parameters ofoptimization if those parameters fell between the step size of theoriginal matrix. Random-walk matrices may also be utilized wherein oncethe parameters have been accurately characterized the matrix may bepopulated by random variation to test whether the original base caseparameters constrained the optimization to potentially non-optimalconfiguration due to basis assumptions that may not have captured all ofthe optimization relationships.

Each component of the array may contribute to the global cost of themachine in a multiplicity of ways. First may be the basis cost of thecomponent. Second may be the derivative costs of the component which mayhave an effect on the cost of other components of the machine. The flowchart shown in FIG. 60 details a base set of variables and therespective interdependencies that may be applied to the optimizationmatrix, including the global array parameters 6002, structural systembasis cost 6004, structural loading 6008, power system cost 6010, nozzlewind load 6012, structural system derivative cost 6014, structuralsystem weight 6018, power system weight 6020, power system derivativecost 6022, power parameters 6024, bearing-yaw system basis cost 6028,system yield 6030, foundation basis cost 6032, system cost 6034,bearing-yaw system 6038, bearing-yaw system derivative cost 6040, andcost unit yield 6042. As can be seen in the flow chart, recursive loopsmay be global or granular to optimize particular sub-systems of themachine and sequentially or non-sequentially the global characteristicsof the machine.

With regard to basis and derivative cost and recursion, the basis costmay be directly derived from the assignment of a “type”. Derivative costmay be indirectly determined by the effect the “type” assignment has onother elements of the system and thereby on the lifetime costs of themachine.

For example, the choice to use a particular copolymer for fabrication ofthe nozzle may have both basis costs and derivative costs. The basiscosts in the case of the nozzle may be the cost of material, the cost offabrication, and the cost of assembly. The derivative costs may be thecost of weight as it relates to the superstructure and substructure, thecost of weight and geometry as it relates to transport, the cost ofgeometry as it relates to manufacture, the cost of environmentaldegradation as it relates to failure and thereby LRC, and the cost ofinstallation. In this case copolymer A may present the lowest cost ofmaterial and fabrication relative to copolymer B. Copolymer A mayhowever contribute more to the weight, LRC, transport, and installationcost than copolymer B. In the case where Copolymer A's basis andderivative costs exceed copolymer B's basis and derivative costs thencopolymer B is more optimal on a cost basis than copolymer A despite thelesser basis cost of copolymer A.

Sometimes the relationship between the basis and derivative costs may besimple as in the case above or complex. Additionally it may be foundthat optimized cost solutions may vary dependent on machine siting or ontimeframe variability of the basis cost. These additional parameters maybe included in a cost optimization derived from a particular site'scharacteristics or from a given basis cost variability measured over agiven timeframe. The variables may include values for availability,market stability, demand and supply variation, and the like.Additionally the basis cost may include stability of supply as avariable. These values may be considered directly as variables incomponent cost or yield models or as coefficients applied to basisvariables.

One example of representing the cost per unit power produced directlyusing matrix tiers may be,Ith, jth cost per unit power produced=((((cost of superstructuretype+cost of Module type+Cost of bearing/yaw system type+cost of powertransfer type+Cost of foundation type)−(summed lifetime operatingcosts))*Annual cost of initial capital)+(summed annual operatingcosts))/Annual yieldWhere, using the superstructure as a representative example,Ith, jth cost of superstructure type=Cost of members+cost ofconnections+cost of installation+cost of LRC+cost of transport+lifetimecost of operation & maintenanceWhere,Cost of members=Sum of n rows' member cost

-   -   Nth row member cost may be determined based on loading values at        the nth row, acceptable slenderness ratio, weight of material in        row for all nth row members, cost of members per unit weight        post fabrication, and material cost variability over time.        Cost of connections=Sum of n rows' connection cost    -   Nth row connection cost may be determined based on loading        values at the nth row connection, weight of material for all nth        row connection, cost of connections per unit weight post        fabrication, and material cost variability over time.        Cost of installation=Sum of n rows' labor cost+cost of equipment        Cost of LRC=(member rate of failure*cost of        replacement(inclusive of equipment and labor))+(connection rate        of failure*cost of replacement (inclusive of equipment and        labor))        Cost of transport=cost of member transport+cost of connection        transport        Cost of operation & maintenance=cost of upkeep and        repair(inclusive of reapplication of treatments over        lifetime)+cost of labor

As may be seen in this example, elements of the superstructure cost maybe dependent on other “type” assignments or global design parameters.For example,

-   Load for a member at the nth row=(dead load (dependent on module    “type”, member “type” and connection “type” load from higher rows,    and power distribution load from higher rows)+environmental load    (dependent on global height, depth, and width parameters,    superstructure “type” load distribution, module “type” wind C_p,    location wind velocity load parameters inclusive of height    variation, location seismic load parameters, and location snow load    parameters))/number of nth row members (dependent on global design    parameters or structural type optimization)

Additionally optimization of the superstructure cost may be dependent onoptimization of the components of superstructure cost prior to inclusionin a higher tier matrix. Cost of installation may be dependent on thecomplexity of connection for a particular member/connection pair type,weight of member type as it effects cost of installation machinery,increased labor and associated insurance costs with specified height ofmachine. Cost of members and connections may be highly dependent on thetypes of superstructure under consideration and the load characteristicsof a particular structure type vs. another. Transport may be dependenton volume of transport means relative to volume used by a member andconnection type and expected location. LRC may be dependent on expectedlocation, type of member and connection used, type of environmentalcoating applied to members and connections, and exposure of members andconnection dependent on module or superstructure types.

Each interrelated and independent optimization may require an individualmatrix of design options that may supply a specific optimal value to ahigher tier matrix variable set. Each tier of optimization matrices mayalso require recursive evaluation.

Another example of representing the cost per unit power produced in aprimary matrix may be,

-   Ith, jth cost per unit power produced=((basis cost of superstructure    type*cost coefficient of array geometry*coefficient of    installation*coefficient of LRC* coefficient transport*coefficient    basis material time variability*coefficient of operation &    maintenance*coefficient of location)+(basis cost of Module    type*coefficient of installation*coefficient of LRC*coefficient    transport*coefficient basis material time variability*coefficient of    operation & maintenance*coefficient of location)+(basis cost of    bearing/yaw system type*cost coefficient of array    geometry*coefficient of installation*coefficient of LRC*coefficient    transport*coefficient of location)+(basis cost of power transfer    type*coefficient of installation*coefficient of LRC*coefficient    transport*coefficient of location)+(basis cost of foundation    type*cost coefficient of array geometry*coefficient of    location))*annual cost of initial capital)/(basis annual yield*yield    coefficient of array geometry)

Where using the coefficient of array geometry as an example,

-   coefficient of array geometry=(cost increase or decrease of wind    load based on array dimensions and nozzle type Cp+cost increase or    decrease of dead load based on array dimensions+cost increase or    decrease of location snow and seismic load based on array    dimensions)/basis cost

Additionally each variable used in calculating the coefficients may befurther decomposed into individual coefficients. Tiered optimizationmatrices and coefficient based matrices may be also be used incombination.

In embodiments, it may be desirable to optimize the yield for a givenmodule by optimizing the integrated function of the accelerating andpower producing components of the module. In short the module yieldoptimization process may be stated as matching of rotor aerodynamicperformance to nozzle aerodynamic performance to generatorcharacteristics such that nozzle acceleration, rotor conversion, andgenerator efficiency are simultaneously maximized across the operatingvelocity range and loading conditions.

A matrix representation was chosen to elucidate the optimization methodbut any optimization representation could be used by those knowledgeablein the art provided it allowed analysis and optimization of thecontributing variables.

Yield optimization for a given module design may be derived from thetesting and comparison of rotor, nozzle, transmission, and generatorcharacteristics over a matrix of loading and velocity inflow conditions.This object may be to optimize the efficiency of component sets over thebroadest possible range of values, or, alternatively, the most prevalentrange of values, within the parameterized operational conditions forloading and inflow velocity by matching rotor design to nozzle design togenerator design wherein the output is optimized by varying the appliedload on the rotor and generator and/or transmission ratio between therotor and the generator to achieve an optimal output. It may desirableto determine the optimal output as an annual, seasonal, or otherperiodic cumulative value vs. an instantaneous value as derived from aWeibull or real set of wind data to determine the maximum possibleannual energy production within the design constraints of thecomponents. The elements effecting annual yield 5302 are detailed inFIG. 61, including baseline module yield characteristics 5304,individual module yield adjustments 6108, operating conditions 6110,rotor inflow velocity 6112, rotor aerodynamic performance 6114,rotor/generator/loaded performance 6118,generator/PE/transmission/loaded performance 6120, intra-arrayperformance 6122, height (ambient velocity) 6124, loading system andpower transfer losses 6128, wind speeds 6130, and grid losses 6132.

A set of rotor designs and types may be selected for an optimizationset. This may be a range within the same general class of blade profilesand geometry or a selection of rotors from different profile and bladegeometry classes or a combinative set. The initial set of rotor designsmay also include rotors having a singular number of blades or a sethaving rotors with different numbers of blades.

The object of this parameterization of conversion characteristics may beto serve as a basis for optimizing rotor geometry to the nozzle or otherspecified conditions. In this regard the aim may be the highestconversion efficiency relative to the lowest flow disturbance. Flowdisturbance may be preliminarily characterized at a maximum by alimiting rpm condition achievable by a given rotor design. Optimizationvariables may include torque imparted to the blade. The rpm and torquevalues may be determined by a force sensor and tachometer coupled to therotor shaft. Bias in the optimization may generally be toward increasedconversion efficiency at the higher velocity ranges and/or the broadestrange of peak conversion values for the rotor or may consider granularoptimization across all inflow conditions as in the case of an adaptiverotor.

A given rotor design's aerodynamic characteristics may be empiricallydetermined as a rotor conversion coefficient under varying loads andvelocities in a duplicative operational environment, in the nozzle casethis may preferably be a closely contained density driven flow. Wherethe characteristics of rotor to power conversion prior to transmission,shaft, or generator losses may be expressed as,C _(—) r,n×m*P _(—) t,m=P _(—) r,n×mOrC _(—) r,n×m=P _(—) r,n×m/P _(—) t,mWhere,P _(—) r,n×m=RPMn×m*t _(—) n×mWhere,

-   C_r, n×m=Conversion coefficient of available fluid power at the nth    loading condition and the mth inflow velocity condition-   P_t, m=Power available in flow at the mth inflow velocity condition-   RPM_n×m=rotor rpm at the nth loading condition and the mth inflow    velocity condition-   t_n×m=shaft torque at the nth loading condition and the mth inflow    velocity condition

An example of a conversion matrix of these values is shown in FIG. 62.

Optimal rotor conversion may be derived from convergence of empiricallyderived rpm and torque characteristics of the rotor at the nth and mthconditions at a maximum value within the matrix.

Evidence of flow disturbance may additionally be gathered by means ofparticulate visualization of the flow at a given operating conditionwherein the properties of the flow may be plotted and the disturbanceeffect on rotor plane throughput may be determined by plotting theparticulate distribution in the flow over time.

A range of n optimized rotor geometries may be selected for the nextstage of optimization.

The range of n optimal rotor geometries may then be tested with a set ofm nozzle geometries. As before the conversion characteristics of therotor-nozzle pair may be determined by coupling a force sensor and atachometer to the rotor shaft.

Nozzle aerodynamic characteristics may be empirically determined by useof anemometers or particulate visualization or the like. The set ofnozzles tested may be of a singular constriction ratio or of multipleconstriction ratios. The set may additionally test both basis andenhanced or complex geometries as described in previous iterations ofthe invention. It may be beneficial to determine basis geometry functioninitially and secondarily enhanced geometries to determine an optimalcombination of basis and enhanced geometries.

An example of an acceleration matrix for 2.75 constriction ratios for 4geometries is shown in FIG. 63.

Since power from a nozzle is dependent on mass throughput or mass flowrate, it may be desirable to characterize the nozzle in terms of massthroughput efficiency, such as shown in FIG. 64.

A nozzle-rotor pair may be tested by the means described above. Fromthis a rotor-nozzle pair conversion matrix may be derived from the rpmand torque matrices at the nth and mth loading and rotor plane inflowconditions and the nozzle efficiency row matrix mass throughput valuesfor a given geometry, such as shown in FIG. 65.

From this a delta matrix between the rotor efficiency and therotor-nozzle pair efficiency may be generated wherein negative valuesmay indicate a reduction in function for the nozzle-rotor pair vs. therotor alone, such as shown in FIG. 66.

A negative value in the delta matrix may indicate that the flowdisturbance of the rotor at the nth and mth condition is inhibiting thefunction of the nozzle by reducing the mass throughput in the nozzle.This may be used to identify and address design optimization parameterseither for the rotor or the nozzle.

This information may be used to identify the most optimal nozzle-rotorpairings and operating ranges from the initial nozzle and rotor sets.This information may additionally be used recursively at a given steplimit to adjust the design of the selected rotors and nozzles to achievea maximum output level for a nozzle-rotor pair. It may be a particularobject of this recursive process to match higher conversion under largerload for the rotor to this nth and mth boundary conditions of theiterative delta matrices. The recursive process may include partial orcomplete redesigns of the rotors or nozzles to maximize a particularproperty as it pertains to matching the negative boundary to the maximaof the power conversion profile for a given rotor. It may be expectedthat through recursive steps of redesign the negative boundary willchange.

The resultant negative boundary of the delta matrix derived fromrecursive testing and design may indicate the optimum balance of loadand inflow velocity and thereby the optimized output torque to rpm for anozzle-rotor pair.

For these purposes the applied load on the nozzle-rotor pair may becharacterized as the internal resistance of the module generator and theexternal resistance (load) applied to the generator. Additionally in thecase where a transmission is used in the module the conversion of torqueto rpm and the inverse may constitute a portion of the load applied tothe rotor. In the case of storage the means of storage may be managedmodularly to allow the charging load applied to the module to beadjusted to the optimal loading parameter at the mth velocity condition.

As is known in the art generators have optimal efficiencies at adesigned generator rotor rpm range. It may be desirable to match theoptimal rpm of the generator to the optimum rpm of the nozzle-rotorpair. Insofar as this can be designed into the generator itself therpm-torque balance may be used to optimize the initial design of thegenerator. In instances, closely matching the nozzle-rotor pairrpm-torque characteristics to the generator rpm characteristics may notbe possible. In this case the rpm-load parameters of the generator maybe mapped into a matrix as shown in FIG. 67.

The rpm component of the nozzle-rotor pair matrix may be mapped forpurposes of comparison, such as shown in FIG. 68.

Each matrix may be filtered for a local conversion or efficiency maxima.It may be desirable in this case where generator characteristics cannotbe closely matched to the nozzle-rotor optimal torque:rpm ratio, toinclude a variable transmission in the module power assembly. Dependingon the preferred method of operation for the module, e.g. fixed speed orvariable speed or a combination thereof, the differential in thetorque:rpm ratio which may be indicated by the maxima in the respectivematrices can be used to determine the best conversion ratio oftorque:rpm between the nozzle-rotor pair and the generator.

In the case of most generators the maximum efficiency may be expected tobe at the design rpm under no load condition with a decrease inefficiency as it approaches the fully loaded condition or shifts offdesign rpm. In the nozzle-rotor pair the maximum efficiency may bevariable as the aerodynamics of the rotor, the nozzle, and the appliedload combinatively define an optimal torque:rpm ratio for each velocityrange.

In this regard it may be optimal to have the module power assemblyinclude both a variable transmission and power electronics for variablespeed and/or fixed operation. In this case the electrical system may besuch that the load imparted to the machine by demand from the grid isparsed into separate loads applied to individual rows of an array. Inthis case the machine may be allowed to run at variable speed up to theoptimal rpm efficiency range of the generator with imposed load closelymatched to the optimum rpm:torque ratio in the given velocity range.Once the optimum rpm range is reached by the rotor-nozzle pair thevariable transmission may then be used to optimize output from thegenerator by balancing the optimum rpm:torque ratio with the generatorsoptimum range. The control mechanism for this may be where the optimumrange between generator optimum condition and the rpm:torque optimumcondition is subject to output optimization wherein a column matrix ofthe nozzle-rotor pair output for a given velocity range under a range ofloading conditions is subjected to an analysis where the column matrixis clipped at a boundary of the optimal conversion value and the optimumgenerator efficiency rpm value. This data would simultaneously beanalyzed from a nozzle-rotor conversion matrix and the componentnozzle-rotor rpm matrix. This clipped column matrix would then beconverted to an output matrix and applied to the generator rpmefficiency values appropriate to each values' rpm and loadingconditions,P _(—) t,m=RPM_rotor,m*t_rotor,m*C _(—) gen, n×mWhere P_t, RPM_rotor, t_rotor may be defined by a fixed mth matrixcondition (same velocity) and the nth condition (loading) may bevariable, and the C_gen variable may be defined by the rpm (mth) andloading (nth) value within its own matrix, such that the matrix may beconstituted of power output within the velocity range at the definedloading:rpm level and the generator efficiency at the given rpm:loadinglevel as shown below.Where

Resistive Load Nozzle- amps (nth) Rotor RPM  C_r 10   144.7384296 0.171894299 9  257.1278202  0.233045696 8  427.0963804  0.295414841 7 663.3066088  0.350134693 6  963.1953312  0.388015961 5

4 1660.157495  0.389505249 3

2 2186.908715  0.29882951 1 2269.283493  0.236644264 Velocity 21.84646123 21.84646123In this case only 2 values were within the boundary.

Resistive Load Nozzle- amps (nth) Rotor RPM 5 1307.753901 4 1660.157495And by matching the respective matrix values and calculating the poweroutput at each condition,

21.85 m/s C_rn P_t, m C_gen Gen_rpm Load 0.40 2028 0.79 1300 5 0.39 22860.92 1700 4

It may be seen the optimum output may be found in this case at a lowernozzle:rotor conversion at a loading level of 4 due to the generatorperformance within that range. In this case the higher rpm may providethe optimal solution. In other cases the optimal performance may befound at the lower rpm range. The deciding factor of the controller torun in variable speed or fixed state may be the maximum output.

It may useful to then utilize the variable transmission as a loadadjustment factor that allows the nozzle:rotor:generator system tooptimize output dynamically in response to specific conditions. In thisregard it may also be beneficial to have a dual operation system whereinthe variable transmission may add load from some base level greater than0 to optimize the system dynamically but if the demand on the moduleexceeds the base loading level to be dynamically able to adjust theapplied mechanical load to the reduced requirement. In cases it may beuseful to have a system that after the condition for fixed operation ismet still has the capability to switch to variable operation if thenozzle:rotor pair loading that met the generators optimal conditions didnot produce the maximum power output from the generator. This may occurwith generators with wide and relatively flat peak efficiency ranges. Inembodiments, a transmission may be applied that has dual functionallowing increase from an under optimal rotor rpm to generator rpmcondition and decrease from an over optimal rotor rpm and generator rpmcontroller and may be dynamically managed by an rpm:torque controllerand a variable speed controller that may allow operation in either avariable speed or fixed speed state based on the maximal output relativeto operating conditions, rotor, transmission, and generatorcharacteristics.

Power produced in either mode may then be converted and conditioned bythe power electronics (PE) components for delivery to the grid. It maybe advantageous to have the PE housed with the modules or at a hub thatcollects the energy from multiple modules.

The process described above may be performed with multiple rotordesigns, nozzles design and constriction rates, componentconfigurations, and generator designs and then integrated into an annualenergy production model to recursively determine an optimal yield designconfiguration. Methods of matrix optimization analysis may be utilizedto reduce the number of test variations run to recursively determinedesign that will yield the maximum output. The optimum design mayadditionally vary with the height at which a given module configurationis operated.

With regard to cost to yield optimization of the module, the cost ofeach configuration on an all-in component cost basis inclusive of costof materials, cost of manufacture, cost of assembly, LRC cost, cost ofoperations and maintenance, ancillary cost or derivative costs, and costof installation may be calculated with the yield optimization todetermine the design configuration that results in the lowest cost andhighest yield combination. In cases, it may be that a particularapplication places a higher premium on output than cost in someempirically described manner. In these cases the empirical relationshipbetween the importance of yield vs. cost may be applied as a ratio thatwould weight the results of the optimal design toward a particularcombination of cost and yield optimization.

Methods are disclosed by which optimization of a nozzle based onnon-linear calculation of LE and intake wall momentum vectors anddensity-sparsity regions in converging-diverging nozzles in ambient andpressurized conditions may be performed.

In the case of the LE and intake wall momentum vectors initialconditions may be approximated in a two-dimensional model wherein theinitial vector paths may be modeled through multiple collision scenarioswhere the collisions may be calculated at a molecular level or somegross approximation thereof until closely matched non-linear functionsare isolated that describe momentum vector paths within the intake and amean path for a given grouping is derived. Additionally the initial andsteady state conditions of an ambient flow using a non-linear momentumtransfer model based on slice interaction and density variation may bederived to closely match empirical measurements for a density drivenflow for use as the basis environment determining the global parametersof the system under consideration. Other approaches may be used todetermine the basis environment such as n-body simulations wherein themacro variables are replaced with molecular variables. Integration ofthe 2 dimensional model into a 3 dimensional system may be necessary toaccurately describe a specific nozzle embodiment's interaction with aflow. This may be inclusive of modeling not only the bulk geometriccharacteristics of the nozzle but also the more complex topography ofthe nozzle wall with quadric uniform or non-uniform tessellation. Inthis model both wake and density flow types may be integrated into themodel based on statistical momentum flux within variably populatedmatrices and collision parameters that may be elastic or non-elastic innature. Rotor behavior within the system may also be included by eithermodeling the portion of the bulk momentum properties of the flow thatinteract or are effected by the motion of the blades, or modelingspecific momentum vectors by calculating the blade interaction on a timestep basis to determine the effect of the blade's momentum flux on theenvironment of the intake. Momentum flux within the system may beapproximated with a constant or variable steady state variable densitysystem wherein the local and global density effects the flow parametersthrough system and is a constant acting on the vectors of momentum fluxderiving from wall topography and rotor interaction. This model may alsobe used to optimize rotor blade # and profile to reduce oppositionalmomentum vectors' effect within the intake region.

A machine for radial velocity energy extraction, an Angular HorizontalAxis−Circumferential WAM Turbine, is now described.

Referring to FIG. 69, the concept of a radial velocity machine may be touse the properties of an angular HAWT structure and a nozzle structurein combination, such as shown in the two positions FIG. 69A and FIG.69B. While an angular HAWT may not be as efficient as HAWT's in normalstructures, it may be particularly suited for this type of application.

The advantage of a combined structure is the circumferential speed ofthe structure when in motion and power production in the columnar arraysat the radial velocity.

For example, a 50 meter angular HAWT (50 m blade width at the narrowestpoint of the described ellipse under rotation) with an RPM of 15 has acircumferential radial velocity (commonly termed tip speed) ofapproximately 40 m/s. A 75 m would have a circumferential radialvelocity of 59 m/s.

With the a columnar array attached to the outer edge assuming the 50 mcase and a nozzle rating of 2.75 and a actual acceleration of 2.2(accelerated to 86 m/s) with an average of 0.3 conversion of raw poweravailable at the throat, this structure, with 4 columnar arrays, wouldproduce approximately 32 MW of power. For 75 m version with the sameconditions (accelerated to 129 m/s) this would produce 110 MW of power.

The angular blade may be of variable length in rotation to maintain aclean radial path at the circumference. Stress on a variable lengthblade may be alleviated by attachment to a channel in the exteriorarrays allowing the blade to extend in the vertical direction while themachine completes its circuit.

Additionally the machine may be executed with non-uniform proportionsdue to the ellipse formed by the main blades' rotation. The exteriorcolumnar arrays may not need to be limited to the number depicted. Inembodiments, optimization of yield cost may balance the tip speed basedon inflow KE with the angular conversion and the inertia of the radialmass based on the number of columnar arrays and the cost of the totalstructure.

In embodiments, the radial motion may also be achieved by mechanicalgearing from the main rotor and may be achieved by transfer ofelectrical power to a secondary machine.

A method for generator/motor thermal recycling is now disclosed. Agenerator/s or motor/s may be housed in a uniform or variform singlewall or dual-wall or n-wall pressure vessel wherein the exit of thepressure vessel may be constituted of a release channel, a fluid turbinesection for additional power generation, a recycling loop to return themedium to the pressure vessel, and the like.

The vessel may contain a fluid medium where the medium may be athermally absorptive gas, a thermally absorptive fluid, and the like, ora combination thereof. In the case of the single wall vessel thegenerator may rest directly within the vessel the fluid is aerosolizedeither mechanically or by means of thermal energy absorption. In thecase of a dual or n-wall system the generator may be encased in thevessel the inner wall or walls would be comprised of a thermallyconductive material and/or structure and the outer wall may include athermal insulating material and/or structure, and fluid may be housedwithin the walls and aerosolized by mechanical or thermal means.

Referring to FIG. 70, the fluid is intended to cool the generatorwherein the fluid may have thermal properties that allow the absorptionof waste heat from the generator in such a way that excites and expandsthe fluid medium increasing the internal pressure of the vessel, shownincluding a fluid chamber 7002, a generator/motor 7004, a fluidrecycling channel 7008, a fluid collection chamber 7010, an externalwall 7012, an internal wall 7014, thermal turbine 7018, and a fluid pump7020. The fluid may be released at a desired rate through a releasechannel which may include a way to produce medium acceleration to aturbine facility where the thermal energy stored by the medium now inthe form of outlet velocity is converted into power. The medium may thenbe cycled through a cooling chamber that further reduces the medium'stemperature and may then be fed back into the pressure vessel by meansof a uni-directional valve facility.

In the case of load balancing this may be useful as it may allowgenerators/motors to be operated at conditions closer to maximum powertheory while capturing a high proportion of the power normally wasted asthermal energy by a generator wherein the load on the generator may bematched or closely matched to the internal resistance of the generator.This may also be applied to any system that produced sufficient wasteheat to justify the expense of the secondary system.

Referring to FIG. 71, in embodiments the present invention may providefor wind power module optimization through matching of rotor aerodynamicperformance, nozzle aerodynamic performance, and generatorcharacteristics. A wind power module optimization algorithm 7104 may beused to optimize the yield for a wind power module 7102 by optimizingthe integrated function of the acceleration in and power producingcomponents of the wind power module, where the rotor aerodynamicperformance to nozzle aerodynamic performance 7108 may be matched to thegenerator characteristics 7110 such that nozzle acceleration, rotorconversion, and generator efficiency are simultaneously maximized acrossthe operating velocity range and loading conditions of the wind powermodule. In addition, a wind power module may be provided with a nozzleoptimized to provide high efficiency for a selected range of windconditions, with generator characteristics optimized to provide highefficiency for a selected range of wind condition, and the like. Thewind power module optimization may be derived from the testing andcomparison of at least two of a rotor, nozzle, transmission, andgenerator characteristics over a matrix of loading and velocity inflowconditions. The wind power module optimization may optimize theefficiency of component sets over the broadest possible range of valueswithin the parameterized operational conditions for loading and inflowvelocity by matching rotor design to nozzle design to generator design.The wind power module output may be optimized by varying the appliedload on the rotor and generator to achieve an optimal output. The windpower module output may be optimized by varying the transmission ratiobetween the rotor and the generator to achieve an optimal output. Thewind power module optimization may be performed with multiple rotordesigns, nozzle design, constriction rates, component configurations,and generator designs, and then integrated into an annual energyproduction model to recursively determine an optimal yield designconfiguration. In embodiments the present invention may provide for awind power module optimization facility 7100 for optimizing the yieldfor a wind power module 7102 by optimizing the integrated function ofthe acceleration in and power producing components of the wind powermodule, where the rotor aerodynamic performance to nozzle aerodynamicperformance 7108 may be matched to the generator characteristics 7110such that nozzle acceleration, rotor conversion, and generatorefficiency are simultaneously maximized across the operating velocityrange and loading conditions of the wind power module. In addition, awind power module may be provided with a nozzle optimized to providehigh efficiency for a selected range of wind conditions, with generatorcharacteristics optimized to provide high efficiency for a selectedrange of wind condition, and the like. The wind power moduleoptimization facility may provide for an algorithm 7104 for performingthe optimization.

Referring to FIG. 72, in embodiments the present invention may provide awind turbine structure consisting of fixed exterior perimetersuperstructure and rotating internal array structure. A wind powersupport structure 7202 may comprise a fixed position superstructure 7204and a plurality of rotating wind power structures 7208, where theplurality of rotating wind power structures are positioned in thestructure of the fixed position superstructure through a bearingfacility. The fixed position superstructure may be mounted to theground. The rotating wind power structure may be a single wind powerturbine module, a row of wind power turbine modules, a column of windpower turbine modules, an array of wind power turbine modules, removablefrom the superstructure, and the like. The wind power support structuremay reduce the torque experienced by the superstructure from variationin inflow vectors in the vertical plane, increase safety, decreaseloading on individual bearing mechanisms, increase load isolation. Thefixed position superstructure may have a cross section, such as arectangle, a polygon, and the like, where the polygon may be ann-pointed regular polygon, an n-pointed irregular polygon. Thecross-section of the shape may be circular. The fixed positionsuperstructure may be a polyhedral, such as a regular polyhedral, anon-regular polyhedral, a prismatic polyhedral, an anti-prismaticpolyhedral, and the like. The fixed position superstructure may have astructural variation, such as a geodesic variation, a tensegrityvariation. The structural variation may be a height variation thatvaries the shape of the fixed position superstructure as a function ofthe height. The height variation may be a change in n of an n-pointedpolygon.

Referring to FIG. 73, in embodiments the present invention may providewind turbine modules with neutral buoyancy structures. A wind powernozzle 7302 may have an integrated buoyancy facility 7304, where thebuoyancy facility contains at least one of a plurality of fluid volumes7308 used to achieve a buoyant condition for the wind power structure.The fluid may be helium, hydrogen, and the like. The fluid may be heatedto alter buoyancy. The heating may provide buoyancy to the nozzle suchthat at least a portion of the dead load of the wind power structure maybe neutralized by buoyancy. The fluid may be pumped to alter buoyancy.The pumping may provide buoyancy to the nozzle such that at least aportion of the dead load of the wind power structure may be neutralizedby buoyancy. The integrated buoyancy facility may be integrated with theinterior surface of the nozzle. In embodiments, a wind power nozzle withan integrated buoyancy facility may be provided, where the buoyancyfacility contains a buoyant material used to achieve a buoyant conditionfor the wind power structure. The buoyant material may be a gasimpregnated foam, where the gas may be hydrogen, helium, and the like.In embodiments, a wind power nozzle with an attached buoyancy facilitymay be provided, where the tethered buoyancy facility contains a buoyantgas used to achieve a buoyant condition for the wind power structure,such as with hydrogen, helium, and the like. The attached may be atethered attachment.

Referring to FIG. 74, in embodiments the present invention may providefor a wind power structure consisting of a fractal support structureinterconnection scheme. A wind power support structure 7402 may comprisea fractal space frame 7404, where the geometric structure of the spaceframe may be repeated in the members 7408 of the space frame to the nthiteration, and where the nth iteration may be the base member and thepolyhedron that forms the basis of the nth iteration member may be thebasis polyhedron. The fractal space frame may be a 3-dimensionalfractal. The fractal space frame may use a regular polyhedral structure,a Reuleaux polyhedral structure, a Kepler-Poinsot polyhedral structure,and the like. The fractal space frame may provide a low solidityrelative to structural and loading capacity thereby reducing the weightof the support structure.

Referring to FIG. 75, in embodiments the present invention may providefor a wind power system that makes use of a variable transmission and PEto balance loading and run at variable speed at the same time. A windpower system 7502 may comprise a variable transmission 7504 in the windpower system that may be in part used to increase the load on a rotor7508 of the wind power system in order to slow the rotor's angularvelocity 7510 in high wind conditions in order to optimize performanceof the wind power system, where the transmission provides forcontinuously variable speed of the rotor. The variable transmission maybe a continuously variable transmission. The optimized performance maybe achieved through a reduction of aerodynamic losses during theextraction of energy from the wind flow through the wind power system.The optimized performance may be achieved through a increased powerconversion by the wind power system. The high wind conditions may be acondition that creates high circumferential speed of the rotor. Thecircumferential speed of the rotor may be decreased to below a low sonicspeed by the increase in load on the rotor. The load may be mechanical,electrical, or a combination of electrical and mechanical loading. Theload on the rotor may be altered through an optimization of a powertransfer network by use of an algorithm that changes a networkcondition. The network condition may be a connection within the networktopography, a resistance through a connection type within the networktopography, and the like. The algorithm may utilize a combinatorialtechnique, a dynamic programming technique, an evolutionary approach,and the like. The performance may be optimized through dynamicallycalculating an increased torque from a baseline load. The variabletransmission may operate bi-directionally with regard to increasing ordecreasing RPM of the rotors. The variable transmission may be a gearedtransmission, a continuous variable transmission, and the like. Therotor may be a wind rotor, a generator rotor, and the like. Inembodiments, a wind power system may comprise a variable transmission tobalance rpm: torque characteristics of the wind power system and a powerelectronics facility, where the variable transmission and powerelectronics facility enable variable or fixed speed operation based on amaximum output algorithm. In embodiments, a wind power system maycomprise a variable transmission to balance rpm and torquecharacteristics of the wind power system and a power electronicsfacility, where the variable transmission and power electronics facilityenable at least one of variable and fixed speed operation based on amaximum output algorithm, and where the maximum output algorithm yieldsmaximum combinative efficiency of applied conditions and systemoperation state.

Referring to FIG. 76, in embodiments the present invention may providefor a wind power system cost-yield optimization facility. A wind powersystem cost-yield optimization algorithm 7602 may optimize the cost ofthe wind power system 7604 with respect to the energy producing yield7608 for the wind power system by employing permutations of possibledesign solutions identified in an n dimensional optimization matrix,where the dimensional number of the matrix may be determined by thenumber of optimization parameters under consideration. In addition,building a wind power system may be optimized for a selected range ofwind conditions based on the cost-yield optimization algorithm. Eachmatrix value may represent a weighted cost per unit of power producedfor a given design implementation that captures a system parameter. Thesystem parameter may be a cost parameter, such as a basic costparameter, a derivative cost parameter, a yield parameter, and the like.The permutations may be recursive loops in the cost-yield optimizationalgorithm, where the recursive loops may optimize a plurality ofsub-systems of the wind power system. A wind power system cost-yieldoptimization facility 7600 may optimize the cost of the wind powersystem 7604 with respect to the energy producing yield 7608 for the windpower system by employing permutations of possible design solutionsidentified in an n dimensional optimization matrix, where thedimensional number of the matrix may be determined by the number ofoptimization parameters under consideration. In addition, building awind power system may be optimized for a selected range of windconditions based on a cost-yield optimization algorithm 7602.

The methods and systems described herein may be deployed in part or inwhole through a machine that executes computer software, program codes,and/or instructions on a processor. The present invention may beimplemented as a method on the machine, as a system or apparatus as partof or in relation to the machine, or as a computer program productembodied in a computer readable medium executing on one or more of themachines. The processor may be part of a server, client, networkinfrastructure, mobile computing platform, stationary computingplatform, or other computing platform. A processor may be any kind ofcomputational or processing device capable of executing programinstructions, codes, binary instructions and the like. The processor maybe or include a signal processor, digital processor, embedded processor,microprocessor or any variant such as a co-processor (math co-processor,graphic co-processor, communication co-processor and the like) and thelike that may directly or indirectly facilitate execution of programcode or program instructions stored thereon. In addition, the processormay enable execution of multiple programs, threads, and codes. Thethreads may be executed simultaneously to enhance the performance of theprocessor and to facilitate simultaneous operations of the application.By way of implementation, methods, program codes, program instructionsand the like described herein may be implemented in one or more thread.The thread may spawn other threads that may have assigned prioritiesassociated with them; the processor may execute these threads based onpriority or any other order based on instructions provided in theprogram code. The processor may include memory that stores methods,codes, instructions and programs as described herein and elsewhere. Theprocessor may access a storage medium through an interface that maystore methods, codes, and instructions as described herein andelsewhere. The storage medium associated with the processor for storingmethods, programs, codes, program instructions or other type ofinstructions capable of being executed by the computing or processingdevice may include but may not be limited to one or more of a CD-ROM,DVD, memory, hard disk, flash drive, RAM, ROM, cache and the like.

A processor may include one or more cores that may enhance speed andperformance of a multiprocessor. In embodiments, the process may be adual core processor, quad core processors, other chip-levelmultiprocessor and the like that combine two or more independent cores(called a die).

The methods and systems described herein may be deployed in part or inwhole through a machine that executes computer software on a server,client, firewall, gateway, hub, router, or other such computer and/ornetworking hardware. The software program may be associated with aserver that may include a file server, print server, domain server,internet server, intranet server and other variants such as secondaryserver, host server, distributed server and the like. The server mayinclude one or more of memories, processors, computer readable media,storage media, ports (physical and virtual), communication devices, andinterfaces capable of accessing other servers, clients, machines, anddevices through a wired or a wireless medium, and the like. The methods,programs or codes as described herein and elsewhere may be executed bythe server. In addition, other devices required for execution of methodsas described in this application may be considered as a part of theinfrastructure associated with the server.

The server may provide an interface to other devices including, withoutlimitation, clients, other servers, printers, database servers, printservers, file servers, communication servers, distributed servers andthe like. Additionally, this coupling and/or connection may facilitateremote execution of program across the network. The networking of someor all of these devices may facilitate parallel processing of a programor method at one or more location without deviating from the scope ofthe invention. In addition, any of the devices attached to the serverthrough an interface may include at least one storage medium capable ofstoring methods, programs, code and/or instructions. A centralrepository may provide program instructions to be executed on differentdevices. In this implementation, the remote repository may act as astorage medium for program code, instructions, and programs.

The software program may be associated with a client that may include afile client, print client, domain client, internet client, intranetclient and other variants such as secondary client, host client,distributed client and the like. The client may include one or more ofmemories, processors, computer readable media, storage media, ports(physical and virtual), communication devices, and interfaces capable ofaccessing other clients, servers, machines, and devices through a wiredor a wireless medium, and the like. The methods, programs or codes asdescribed herein and elsewhere may be executed by the client. Inaddition, other devices required for execution of methods as describedin this application may be considered as a part of the infrastructureassociated with the client.

The client may provide an interface to other devices including, withoutlimitation, servers, other clients, printers, database servers, printservers, file servers, communication servers, distributed servers andthe like. Additionally, this coupling and/or connection may facilitateremote execution of program across the network. The networking of someor all of these devices may facilitate parallel processing of a programor method at one or more location without deviating from the scope ofthe invention. In addition, any of the devices attached to the clientthrough an interface may include at least one storage medium capable ofstoring methods, programs, applications, code and/or instructions. Acentral repository may provide program instructions to be executed ondifferent devices. In this implementation, the remote repository may actas a storage medium for program code, instructions, and programs.

The methods and systems described herein may be deployed in part or inwhole through network infrastructures. The network infrastructure mayinclude elements such as computing devices, servers, routers, hubs,firewalls, clients, personal computers, communication devices, routingdevices and other active and passive devices, modules and/or componentsas known in the art. The computing and/or non-computing device(s)associated with the network infrastructure may include, apart from othercomponents, a storage medium such as flash memory, buffer, stack, RAM,ROM and the like. The processes, methods, program codes, instructionsdescribed herein and elsewhere may be executed by one or more of thenetwork infrastructural elements.

The methods, program codes, and instructions described herein andelsewhere may be implemented on a cellular network having multiplecells. The cellular network may either be frequency division multipleaccess (FDMA) network or code division multiple access (CDMA) network.The cellular network may include mobile devices, cell sites, basestations, repeaters, antennas, towers, and the like. The cell networkmay be a GSM, GPRS, 3G, EVDO, mesh, or other networks types.

The methods, programs codes, and instructions described herein andelsewhere may be implemented on or through mobile devices. The mobiledevices may include navigation devices, cell phones, mobile phones,mobile personal digital assistants, laptops, palmtops, netbooks, pagers,electronic books readers, music players and the like. These devices mayinclude, apart from other components, a storage medium such as a flashmemory, buffer, RAM, ROM and one or more computing devices. Thecomputing devices associated with mobile devices may be enabled toexecute program codes, methods, and instructions stored thereon.Alternatively, the mobile devices may be configured to executeinstructions in collaboration with other devices. The mobile devices maycommunicate with base stations interfaced with servers and configured toexecute program codes. The mobile devices may communicate on a peer topeer network, mesh network, or other communications network. The programcode may be stored on the storage medium associated with the server andexecuted by a computing device embedded within the server. The basestation may include a computing device and a storage medium. The storagedevice may store program codes and instructions executed by thecomputing devices associated with the base station.

The computer software, program codes, and/or instructions may be storedand/or accessed on machine readable media that may include: computercomponents, devices, and recording media that retain digital data usedfor computing for some interval of time; semiconductor storage known asrandom access memory (RAM); mass storage typically for more permanentstorage, such as optical discs, forms of magnetic storage like harddisks, tapes, drums, cards and other types; processor registers, cachememory, volatile memory, non-volatile memory; optical storage such asCD, DVD; removable media such as flash memory (e.g. USB sticks or keys),floppy disks, magnetic tape, paper tape, punch cards, standalone RAMdisks, Zip drives, removable mass storage, off-line, and the like; othercomputer memory such as dynamic memory, static memory, read/writestorage, mutable storage, read only, random access, sequential access,location addressable, file addressable, content addressable, networkattached storage, storage area network, bar codes, magnetic ink, and thelike.

The methods and systems described herein may transform physical and/oror intangible items from one state to another. The methods and systemsdescribed herein may also transform data representing physical and/orintangible items from one state to another.

The elements described and depicted herein, including in flow charts andblock diagrams throughout the figures, imply logical boundaries betweenthe elements. However, according to software or hardware engineeringpractices, the depicted elements and the functions thereof may beimplemented on machines through computer executable media having aprocessor capable of executing program instructions stored thereon as amonolithic software structure, as standalone software modules, or asmodules that employ external routines, code, services, and so forth, orany combination of these, and all such implementations may be within thescope of the present disclosure. Examples of such machines may include,but may not be limited to, personal digital assistants, laptops,personal computers, mobile phones, other handheld computing devices,medical equipment, wired or wireless communication devices, transducers,chips, calculators, satellites, tablet PCs, electronic books, gadgets,electronic devices, devices having artificial intelligence, computingdevices, networking equipments, servers, routers and the like.Furthermore, the elements depicted in the flow chart and block diagramsor any other logical component may be implemented on a machine capableof executing program instructions. Thus, while the foregoing drawingsand descriptions set forth functional aspects of the disclosed systems,no particular arrangement of software for implementing these functionalaspects should be inferred from these descriptions unless explicitlystated or otherwise clear from the context. Similarly, it will beappreciated that the various steps identified and described above may bevaried, and that the order of steps may be adapted to particularapplications of the techniques disclosed herein. All such variations andmodifications are intended to fall within the scope of this disclosure.As such, the depiction and/or description of an order for various stepsshould not be understood to require a particular order of execution forthose steps, unless required by a particular application, or explicitlystated or otherwise clear from the context.

The methods and/or processes described above, and steps thereof, may berealized in hardware, software or any combination of hardware andsoftware suitable for a particular application. The hardware may includea general purpose computer and/or dedicated computing device or specificcomputing device or particular aspect or component of a specificcomputing device. The processes may be realized in one or moremicroprocessors, microcontrollers, embedded microcontrollers,programmable digital signal processors or other programmable device,along with internal and/or external memory. The processes may also, orinstead, be embodied in an application specific integrated circuit, aprogrammable gate array, programmable array logic, or any other deviceor combination of devices that may be configured to process electronicsignals. It will further be appreciated that one or more of theprocesses may be realized as a computer executable code capable of beingexecuted on a machine readable medium.

The computer executable code may be created using a structuredprogramming language such as C, an object oriented programming languagesuch as C++, or any other high-level or low-level programming language(including assembly languages, hardware description languages, anddatabase programming languages and technologies) that may be stored,compiled or interpreted to run on one of the above devices, as well asheterogeneous combinations of processors, processor architectures, orcombinations of different hardware and software, or any other machinecapable of executing program instructions.

Thus, in one aspect, each method described above and combinationsthereof may be embodied in computer executable code that, when executingon one or more computing devices, performs the steps thereof. In anotheraspect, the methods may be embodied in systems that perform the stepsthereof, and may be distributed across devices in a number of ways, orall of the functionality may be integrated into a dedicated, standalonedevice or other hardware. In another aspect, the means for performingthe steps associated with the processes described above may include anyof the hardware and/or software described above. All such permutationsand combinations are intended to fall within the scope of the presentdisclosure.

While the invention has been disclosed in connection with the preferredembodiments shown and described in detail, various modifications andimprovements thereon will become readily apparent to those skilled inthe art. Accordingly, the spirit and scope of the present invention isnot to be limited by the foregoing examples, but is to be understood inthe broadest sense allowable by law.

All documents referenced herein are hereby incorporated by reference.

What is claimed is:
 1. A wind power support structure, comprising: afixed position superstructure; and a plurality of wind power turbinemodules, wherein each of the plurality of wind power turbine modules ismounted on a rotating bearing facility in the fixed positionsuperstructure such as to allow each one of the wind power turbinemodules to rotate to a wind direction independently of the other ones ofthe plurality of wind power turbine modules, and wherein each one of theplurality of wind power turbine modules includes a nozzle for windacceleration, a turbine, and a mechanical-to-electrical power conversionfacility.
 2. The support structure of claim 1, wherein the fixedposition superstructure is mounted to the ground.
 3. The supportstructure of claim 1, wherein the plurality of wind power turbinemodules are arranged in a plurality of rows of wind power turbinemodules, each row of wind power turbine modules including one or morewind power turbine modules mounted to a rotating bearing facility in thefixed position superstructure such as to allow each of the rows torotate to the wind direction independently of the other of the pluralityof rows.
 4. The support structure of claim 1, wherein the plurality ofwind power turbine modules is arranged as a column of single wind powerturbine modules, wherein each of the plurality of wind power turbinemodules is mounted such as to allow each of the plurality of wind powerturbine modules to rotate to the wind direction independently.
 5. Thesupport structure of claim 1, wherein the plurality of wind powerturbine modules is a row and column array of wind power turbine modules.6. The support structure of claim 1, wherein at least one of theplurality of wind power turbine modules is removable from thesuperstructure.
 7. The support structure of claim 1, wherein the windpower support structure reduces the torque experienced by thesuperstructure from variation in inflow vectors in the vertical plane.8. The support structure of claim 1, wherein the wind power supportstructure increases safety.
 9. The support structure of claim 1, whereinthe wind power support structure decreases loading on individual bearingmechanisms.
 10. The support structure of claim 1, wherein the wind powersupport structure increases load isolation.
 11. The support structure ofclaim 1, wherein the fixed position superstructure has a cross section.12. The support structure of claim 11, wherein the cross-section is arectangle.
 13. The support structure of claim 11, wherein thecross-section is a polygon.
 14. The support structure of claim 13,wherein the polygon is an n-pointed regular polygon.
 15. The supportstructure of claim 13, wherein the polygon is an n-pointed irregularpolygon.
 16. The support structure of claim 11, wherein thecross-section of the shape is circular.
 17. The support structure ofclaim 1, wherein the fixed position superstructure is a polyhedral. 18.The support structure of claim 17, wherein the polyhedral is a regularpolyhedral.
 19. The support structure of claim 17, wherein thepolyhedral is a non-regular polyhedral.
 20. The support structure ofclaim 17, wherein the polyhedral is a prismatic polyhedral.
 21. Thesupport structure of claim 17, wherein the polyhedral is ananti-prismatic polyhedral.
 22. The support structure of claim 1, whereinthe fixed position superstructure has a structural variation.
 23. Thesupport structure of claim 22, wherein the structural variation is ageodesic variation.
 24. The support structure of claim 22, wherein thestructural variation is a tensegrity variation.
 25. The supportstructure of claim 22, wherein the structural variation is a heightvariation that varies the shape of the fixed position superstructure asa function of the height.
 26. The support structure of claim 25, whereinthe height variation is a change in n of an n-pointed polygon.